S1014 (s1014-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S1014 (s1014-il) Reynolds number: 1,000,000 Max Cl/Cd: 54.89 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1014-il-1000000.txt Download as CSV file: xf-s1014-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S1014
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -1.2261 0.07322 0.06899 -0.0550 0.8872 0.0169
-19.500 -1.2450 0.06739 0.06298 -0.0573 0.8759 0.0172
-19.250 -1.2554 0.06289 0.05834 -0.0588 0.8680 0.0174
-19.000 -1.2629 0.05899 0.05430 -0.0599 0.8612 0.0176
-18.750 -1.2671 0.05554 0.05075 -0.0607 0.8566 0.0180
-18.500 -1.2692 0.05248 0.04760 -0.0612 0.8524 0.0183
-18.250 -1.2681 0.04992 0.04493 -0.0615 0.8484 0.0186
-18.000 -1.2653 0.04764 0.04255 -0.0615 0.8448 0.0190
-17.750 -1.2600 0.04563 0.04046 -0.0615 0.8424 0.0194
-17.500 -1.2557 0.04358 0.03833 -0.0613 0.8399 0.0197
-17.250 -1.2471 0.04202 0.03668 -0.0610 0.8374 0.0201
-17.000 -1.2426 0.04015 0.03472 -0.0606 0.8351 0.0203
-16.750 -1.2451 0.03777 0.03225 -0.0596 0.8328 0.0210
-16.500 -1.2391 0.03618 0.03060 -0.0589 0.8306 0.0217
-16.250 -1.2305 0.03484 0.02919 -0.0581 0.8284 0.0222
-16.000 -1.2195 0.03368 0.02800 -0.0575 0.8271 0.0230
-15.750 -1.2097 0.03247 0.02672 -0.0567 0.8258 0.0235
-15.500 -1.1977 0.03144 0.02563 -0.0560 0.8243 0.0240
-15.250 -1.1909 0.03008 0.02422 -0.0548 0.8229 0.0251
-15.000 -1.1807 0.02898 0.02309 -0.0538 0.8215 0.0260
-14.750 -1.1689 0.02802 0.02209 -0.0528 0.8201 0.0268
-14.500 -1.1552 0.02721 0.02123 -0.0520 0.8188 0.0279
-14.250 -1.1400 0.02650 0.02046 -0.0512 0.8175 0.0287
-14.000 -1.1297 0.02549 0.01942 -0.0499 0.8162 0.0300
-13.750 -1.1168 0.02468 0.01859 -0.0488 0.8149 0.0315
-13.500 -1.1014 0.02403 0.01790 -0.0479 0.8134 0.0328
-13.250 -1.0844 0.02348 0.01729 -0.0471 0.8119 0.0338
-13.000 -1.0717 0.02265 0.01645 -0.0459 0.8111 0.0357
-12.750 -1.0563 0.02199 0.01580 -0.0449 0.8103 0.0374
-12.500 -1.0392 0.02144 0.01521 -0.0441 0.8095 0.0389
-12.250 -1.0208 0.02097 0.01471 -0.0433 0.8087 0.0401
-12.000 -1.0068 0.02026 0.01400 -0.0421 0.8078 0.0426
-11.750 -0.9897 0.01972 0.01345 -0.0411 0.8070 0.0445
-11.500 -0.9709 0.01929 0.01300 -0.0404 0.8061 0.0464
-11.250 -0.9538 0.01876 0.01246 -0.0394 0.8052 0.0486
-11.000 -0.9369 0.01823 0.01194 -0.0383 0.8044 0.0512
-10.750 -0.9182 0.01780 0.01150 -0.0375 0.8035 0.0534
-10.500 -0.8985 0.01744 0.01110 -0.0367 0.8027 0.0552
-10.250 -0.8818 0.01692 0.01059 -0.0355 0.8019 0.0588
-10.000 -0.8630 0.01651 0.01019 -0.0346 0.8012 0.0617
-9.750 -0.8426 0.01619 0.00984 -0.0339 0.8004 0.0640
-9.500 -0.8252 0.01572 0.00939 -0.0327 0.7996 0.0683
-9.250 -0.8062 0.01535 0.00903 -0.0318 0.7989 0.0719
-9.000 -0.7858 0.01505 0.00871 -0.0310 0.7982 0.0750
-8.750 -0.7679 0.01464 0.00834 -0.0298 0.7973 0.0807
-8.500 -0.7481 0.01434 0.00804 -0.0289 0.7965 0.0846
-8.250 -0.7289 0.01403 0.00775 -0.0279 0.7955 0.0901
-8.000 -0.7097 0.01369 0.00743 -0.0269 0.7950 0.0957
-7.750 -0.6898 0.01337 0.00713 -0.0260 0.7944 0.1013
-7.500 -0.6709 0.01302 0.00682 -0.0248 0.7940 0.1085
-7.250 -0.6511 0.01273 0.00654 -0.0238 0.7934 0.1153
-7.000 -0.6323 0.01240 0.00626 -0.0226 0.7929 0.1235
-6.750 -0.6134 0.01209 0.00599 -0.0214 0.7923 0.1321
-6.250 -0.5771 0.01147 0.00547 -0.0187 0.7910 0.1536
-6.000 -0.5604 0.01117 0.00523 -0.0170 0.7903 0.1668
-5.750 -0.5447 0.01091 0.00504 -0.0150 0.7896 0.1811
-5.500 -0.5301 0.01069 0.00489 -0.0128 0.7888 0.1974
-5.250 -0.5139 0.01044 0.00473 -0.0109 0.7881 0.2183
-5.000 -0.4965 0.01014 0.00455 -0.0092 0.7872 0.2441
-4.750 -0.4784 0.00983 0.00437 -0.0077 0.7864 0.2736
-4.500 -0.4615 0.00946 0.00418 -0.0060 0.7857 0.3139
-4.250 -0.4448 0.00905 0.00398 -0.0042 0.7850 0.3615
-4.000 -0.4285 0.00859 0.00376 -0.0024 0.7843 0.4194
-3.750 -0.4134 0.00803 0.00350 -0.0004 0.7836 0.4911
-3.500 -0.3985 0.00741 0.00323 0.0018 0.7829 0.5740
-3.250 -0.3816 0.00696 0.00320 0.0037 0.7820 0.6699
-3.000 -0.3536 0.00703 0.00331 0.0037 0.7813 0.6991
-2.750 -0.3247 0.00714 0.00341 0.0034 0.7808 0.7116
-2.500 -0.2956 0.00729 0.00355 0.0031 0.7801 0.7196
-2.250 -0.2668 0.00748 0.00372 0.0029 0.7790 0.7265
-2.000 -0.2376 0.00759 0.00382 0.0025 0.7784 0.7315
-1.750 -0.2078 0.00768 0.00393 0.0021 0.7778 0.7354
-1.500 -0.1782 0.00778 0.00403 0.0017 0.7770 0.7397
-1.250 -0.1487 0.00786 0.00410 0.0013 0.7760 0.7434
-1.000 -0.1194 0.00790 0.00413 0.0009 0.7746 0.7464
-0.750 -0.0896 0.00792 0.00418 0.0006 0.7729 0.7494
-0.500 -0.0597 0.00794 0.00421 0.0003 0.7701 0.7527
-0.250 -0.0295 0.00788 0.00412 0.0001 0.7663 0.7566
0.000 0.0000 0.00796 0.00414 0.0000 0.7612 0.7612
0.250 0.0295 0.00788 0.00412 -0.0001 0.7565 0.7663
0.500 0.0596 0.00794 0.00421 -0.0003 0.7527 0.7701
0.750 0.0896 0.00792 0.00418 -0.0006 0.7494 0.7730
1.000 0.1194 0.00790 0.00413 -0.0009 0.7464 0.7746
1.250 0.1487 0.00786 0.00410 -0.0013 0.7434 0.7760
1.500 0.1781 0.00778 0.00403 -0.0017 0.7397 0.7770
1.750 0.2078 0.00768 0.00393 -0.0021 0.7354 0.7778
2.000 0.2375 0.00759 0.00382 -0.0025 0.7315 0.7784
2.250 0.2668 0.00748 0.00372 -0.0029 0.7266 0.7790
2.500 0.2955 0.00729 0.00355 -0.0031 0.7196 0.7801
2.750 0.3246 0.00714 0.00341 -0.0034 0.7116 0.7808
3.000 0.3536 0.00703 0.00331 -0.0037 0.6991 0.7813
3.250 0.3815 0.00695 0.00319 -0.0037 0.6693 0.7820
3.500 0.3985 0.00741 0.00323 -0.0017 0.5737 0.7829
3.750 0.4133 0.00804 0.00351 0.0004 0.4905 0.7836
4.000 0.4283 0.00860 0.00376 0.0024 0.4184 0.7843
4.250 0.4448 0.00905 0.00398 0.0042 0.3619 0.7850
4.500 0.4614 0.00946 0.00418 0.0060 0.3134 0.7857
4.750 0.4784 0.00983 0.00437 0.0077 0.2737 0.7864
5.000 0.4965 0.01014 0.00455 0.0092 0.2441 0.7872
5.250 0.5139 0.01044 0.00473 0.0109 0.2184 0.7881
5.500 0.5302 0.01068 0.00489 0.0128 0.1977 0.7888
5.750 0.5448 0.01091 0.00504 0.0150 0.1810 0.7896
6.000 0.5603 0.01117 0.00523 0.0170 0.1665 0.7903
6.250 0.5772 0.01147 0.00547 0.0187 0.1537 0.7910
6.750 0.6137 0.01208 0.00599 0.0214 0.1328 0.7923
7.000 0.6324 0.01240 0.00626 0.0226 0.1237 0.7929
7.250 0.6512 0.01272 0.00654 0.0238 0.1154 0.7934
7.500 0.6710 0.01302 0.00682 0.0248 0.1085 0.7940
7.750 0.6898 0.01337 0.00712 0.0259 0.1013 0.7945
8.000 0.7098 0.01368 0.00743 0.0269 0.0959 0.7950
8.250 0.7291 0.01403 0.00774 0.0279 0.0903 0.7955
8.500 0.7482 0.01434 0.00804 0.0289 0.0847 0.7965
8.750 0.7681 0.01464 0.00833 0.0298 0.0806 0.7973
9.000 0.7860 0.01504 0.00870 0.0310 0.0750 0.7982
9.250 0.8064 0.01534 0.00902 0.0317 0.0719 0.7989
9.500 0.8254 0.01572 0.00939 0.0327 0.0683 0.7996
9.750 0.8430 0.01618 0.00983 0.0338 0.0639 0.8004
10.000 0.8634 0.01649 0.01017 0.0346 0.0618 0.8012
10.250 0.8821 0.01691 0.01059 0.0355 0.0588 0.8019
10.500 0.8988 0.01743 0.01109 0.0367 0.0551 0.8028
10.750 0.9185 0.01780 0.01149 0.0374 0.0534 0.8036
11.000 0.9372 0.01822 0.01193 0.0383 0.0511 0.8044
11.250 0.9542 0.01875 0.01244 0.0393 0.0487 0.8052
11.500 0.9712 0.01928 0.01299 0.0403 0.0464 0.8061
11.750 0.9900 0.01971 0.01345 0.0411 0.0447 0.8070
12.000 1.0071 0.02025 0.01399 0.0420 0.0425 0.8078
12.250 1.0214 0.02095 0.01468 0.0433 0.0400 0.8087
12.500 1.0396 0.02143 0.01521 0.0440 0.0389 0.8095
12.750 1.0567 0.02198 0.01578 0.0449 0.0372 0.8103
13.000 1.0721 0.02265 0.01644 0.0459 0.0355 0.8112
13.250 1.0850 0.02347 0.01727 0.0471 0.0339 0.8119
13.500 1.1020 0.02401 0.01787 0.0478 0.0326 0.8134
13.750 1.1177 0.02464 0.01854 0.0487 0.0314 0.8149
14.000 1.1304 0.02546 0.01938 0.0498 0.0300 0.8162
14.250 1.1408 0.02646 0.02042 0.0511 0.0286 0.8176
14.500 1.1558 0.02719 0.02120 0.0519 0.0279 0.8189
14.750 1.1693 0.02801 0.02208 0.0528 0.0270 0.8202
15.000 1.1814 0.02895 0.02306 0.0537 0.0261 0.8215
15.250 1.1915 0.03006 0.02419 0.0547 0.0250 0.8230
15.500 1.1974 0.03148 0.02567 0.0560 0.0241 0.8244
15.750 1.2106 0.03243 0.02668 0.0566 0.0236 0.8258
16.000 1.2216 0.03354 0.02785 0.0574 0.0230 0.8272
16.250 1.2314 0.03479 0.02915 0.0581 0.0222 0.8284
16.500 1.2394 0.03617 0.03060 0.0588 0.0217 0.8308
16.750 1.2463 0.03769 0.03218 0.0595 0.0212 0.8330
17.000 1.2471 0.03978 0.03434 0.0604 0.0205 0.8352
17.250 1.2514 0.04165 0.03630 0.0609 0.0199 0.8376
17.500 1.2587 0.04333 0.03806 0.0612 0.0197 0.8400
17.750 1.2629 0.04537 0.04019 0.0614 0.0193 0.8426
18.000 1.2676 0.04744 0.04234 0.0614 0.0189 0.8450
18.250 1.2691 0.04985 0.04485 0.0614 0.0186 0.8487
18.500 1.2705 0.05236 0.04747 0.0612 0.0183 0.8527
18.750 1.2683 0.05542 0.05063 0.0607 0.0179 0.8571
19.000 1.2653 0.05870 0.05401 0.0599 0.0177 0.8619
19.250 1.2577 0.06262 0.05807 0.0589 0.0174 0.8689
|
Polar data table (+)
Polar graphs
<< Back to S1014 (s1014-il)