NACA 63(2)A-015 (naca632a015-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 63(2)A-015 (naca632a015-il) Reynolds number: 500,000 Max Cl/Cd: 76.65 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca632a015-il-500000.txt Download as CSV file: xf-naca632a015-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)A-015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4037 0.08003 0.07781 -0.0465 1.0000 0.0256
-11.000 -0.4421 0.06944 0.06716 -0.0526 1.0000 0.0253
-10.750 -0.4797 0.06172 0.05933 -0.0559 1.0000 0.0250
-10.500 -0.5123 0.05612 0.05364 -0.0569 1.0000 0.0250
-10.250 -0.5419 0.05176 0.04917 -0.0564 1.0000 0.0248
-10.000 -0.5669 0.04847 0.04578 -0.0544 1.0000 0.0249
-9.750 -0.5914 0.04577 0.04298 -0.0509 1.0000 0.0248
-9.500 -0.6138 0.04379 0.04095 -0.0459 1.0000 0.0250
-9.250 -0.6340 0.04191 0.03901 -0.0403 1.0000 0.0251
-9.000 -0.7725 0.03032 0.02542 -0.0235 0.9933 0.0159
-8.750 -0.7504 0.02565 0.02014 -0.0238 0.9875 0.0161
-8.500 -0.7186 0.02314 0.01730 -0.0253 0.9836 0.0162
-8.250 -0.6886 0.02107 0.01505 -0.0264 0.9766 0.0167
-8.000 -0.6537 0.02018 0.01415 -0.0284 0.9710 0.0172
-7.750 -0.6199 0.01918 0.01308 -0.0300 0.9618 0.0178
-7.500 -0.5810 0.01815 0.01196 -0.0327 0.9553 0.0187
-7.250 -0.5428 0.01725 0.01091 -0.0351 0.9447 0.0197
-7.000 -0.5055 0.01616 0.00982 -0.0377 0.9320 0.0205
-6.750 -0.4702 0.01560 0.00920 -0.0395 0.9154 0.0218
-6.500 -0.4432 0.01497 0.00845 -0.0395 0.8962 0.0228
-6.250 -0.4230 0.01439 0.00777 -0.0382 0.8776 0.0240
-6.000 -0.4021 0.01410 0.00743 -0.0370 0.8611 0.0255
-5.750 -0.3811 0.01383 0.00705 -0.0356 0.8464 0.0273
-5.500 -0.3634 0.01337 0.00655 -0.0337 0.8332 0.0292
-5.250 -0.3409 0.01320 0.00630 -0.0327 0.8218 0.0322
-5.000 -0.3229 0.01276 0.00584 -0.0308 0.8104 0.0355
-4.750 -0.3022 0.01246 0.00547 -0.0294 0.8001 0.0394
-4.500 -0.2800 0.01226 0.00523 -0.0284 0.7907 0.0435
-4.250 -0.2590 0.01195 0.00488 -0.0271 0.7811 0.0469
-3.750 -0.2131 0.01155 0.00440 -0.0251 0.7641 0.0532
-3.500 -0.1913 0.01126 0.00406 -0.0240 0.7562 0.0573
-3.250 -0.1675 0.01108 0.00387 -0.0232 0.7478 0.0621
-3.000 -0.1444 0.01085 0.00360 -0.0222 0.7403 0.0685
-2.750 -0.1208 0.01062 0.00338 -0.0213 0.7326 0.0782
-2.500 -0.1090 0.00956 0.00288 -0.0186 0.7250 0.2422
-2.250 -0.1077 0.00810 0.00254 -0.0139 0.7177 0.5293
-2.000 -0.0861 0.00791 0.00250 -0.0125 0.7100 0.5810
-1.750 -0.0622 0.00785 0.00247 -0.0116 0.7032 0.6124
-1.500 -0.0370 0.00781 0.00246 -0.0109 0.6954 0.6336
-1.250 -0.0115 0.00782 0.00243 -0.0103 0.6885 0.6513
-1.000 0.0139 0.00779 0.00243 -0.0096 0.6800 0.6676
-0.750 0.0389 0.00782 0.00241 -0.0089 0.6701 0.6834
-0.500 0.0638 0.00779 0.00239 -0.0081 0.6578 0.6972
-0.250 0.0888 0.00779 0.00240 -0.0073 0.6469 0.7118
0.000 0.1142 0.00782 0.00240 -0.0067 0.6385 0.7250
0.250 0.1404 0.00784 0.00240 -0.0063 0.6300 0.7349
0.500 0.1670 0.00784 0.00239 -0.0060 0.6218 0.7420
0.750 0.1935 0.00785 0.00239 -0.0056 0.6132 0.7502
1.000 0.2200 0.00786 0.00239 -0.0053 0.6055 0.7577
1.250 0.2465 0.00787 0.00240 -0.0050 0.5970 0.7659
1.500 0.2727 0.00790 0.00240 -0.0046 0.5884 0.7735
1.750 0.2991 0.00790 0.00243 -0.0043 0.5791 0.7817
2.000 0.3251 0.00794 0.00245 -0.0039 0.5708 0.7899
2.250 0.3513 0.00794 0.00249 -0.0035 0.5614 0.7986
2.500 0.3772 0.00798 0.00252 -0.0030 0.5524 0.8072
2.750 0.4029 0.00801 0.00257 -0.0026 0.5420 0.8164
3.000 0.4285 0.00804 0.00262 -0.0021 0.5312 0.8258
3.250 0.4535 0.00811 0.00268 -0.0015 0.5208 0.8364
3.500 0.4791 0.00815 0.00276 -0.0010 0.5092 0.8466
3.750 0.5043 0.00821 0.00284 -0.0005 0.4972 0.8582
4.000 0.5291 0.00828 0.00293 0.0002 0.4838 0.8708
4.250 0.5545 0.00837 0.00304 0.0007 0.4674 0.8837
4.500 0.5802 0.00849 0.00316 0.0011 0.4491 0.8977
4.750 0.6064 0.00867 0.00331 0.0014 0.4270 0.9123
5.000 0.6340 0.00892 0.00349 0.0012 0.3978 0.9268
5.250 0.6622 0.00933 0.00374 0.0008 0.3586 0.9407
5.500 0.6961 0.00983 0.00408 -0.0009 0.3212 0.9495
5.750 0.7285 0.01029 0.00441 -0.0024 0.2956 0.9586
6.000 0.7643 0.01071 0.00475 -0.0045 0.2751 0.9648
6.250 0.7973 0.01110 0.00508 -0.0060 0.2599 0.9719
6.500 0.8333 0.01150 0.00541 -0.0081 0.2467 0.9764
7.000 0.9032 0.01220 0.00606 -0.0120 0.2254 0.9867
7.250 0.9387 0.01257 0.00640 -0.0142 0.2168 0.9914
7.500 0.9750 0.01290 0.00672 -0.0165 0.2078 0.9955
7.750 1.0125 0.01323 0.00705 -0.0190 0.1996 0.9990
8.000 1.0325 0.01347 0.00730 -0.0180 0.1930 1.0000
8.250 1.0418 0.01375 0.00756 -0.0147 0.1877 1.0000
8.500 1.0559 0.01393 0.00777 -0.0123 0.1820 1.0000
8.750 1.0669 0.01424 0.00805 -0.0094 0.1747 1.0000
9.000 1.0813 0.01447 0.00831 -0.0071 0.1684 1.0000
9.250 1.0933 0.01480 0.00862 -0.0044 0.1613 1.0000
9.500 1.1059 0.01508 0.00892 -0.0018 0.1546 1.0000
9.750 1.1140 0.01542 0.00923 0.0016 0.1471 1.0000
10.000 1.1242 0.01574 0.00957 0.0046 0.1394 1.0000
10.250 1.1329 0.01619 0.00999 0.0076 0.1309 1.0000
10.500 1.1431 0.01667 0.01045 0.0103 0.1211 1.0000
10.750 1.1526 0.01724 0.01100 0.0129 0.1112 1.0000
11.000 1.1610 0.01792 0.01165 0.0155 0.1018 1.0000
11.250 1.1683 0.01873 0.01243 0.0180 0.0931 1.0000
11.500 1.1755 0.01963 0.01330 0.0202 0.0852 1.0000
11.750 1.1846 0.02049 0.01419 0.0222 0.0789 1.0000
12.000 1.1904 0.02162 0.01529 0.0242 0.0731 1.0000
12.250 1.2006 0.02255 0.01627 0.0257 0.0690 1.0000
12.500 1.2079 0.02373 0.01747 0.0272 0.0651 1.0000
12.750 1.2149 0.02500 0.01878 0.0285 0.0619 1.0000
13.000 1.2236 0.02622 0.02005 0.0296 0.0587 1.0000
13.250 1.2280 0.02781 0.02165 0.0308 0.0559 1.0000
13.500 1.2333 0.02940 0.02331 0.0318 0.0534 1.0000
13.750 1.2402 0.03092 0.02490 0.0325 0.0512 1.0000
14.000 1.2428 0.03286 0.02687 0.0333 0.0490 1.0000
14.250 1.2383 0.03548 0.02952 0.0341 0.0469 1.0000
14.500 1.2448 0.03721 0.03137 0.0344 0.0453 1.0000
14.750 1.2479 0.03928 0.03352 0.0348 0.0439 1.0000
15.000 1.2486 0.04166 0.03596 0.0350 0.0426 1.0000
15.250 1.2461 0.04443 0.03878 0.0350 0.0415 1.0000
15.500 1.2391 0.04772 0.04213 0.0350 0.0404 1.0000
15.750 1.2375 0.05058 0.04510 0.0348 0.0395 1.0000
16.000 1.2394 0.05316 0.04778 0.0344 0.0388 1.0000
16.250 1.2404 0.05592 0.05064 0.0339 0.0378 1.0000
16.500 1.2391 0.05898 0.05378 0.0333 0.0371 1.0000
16.750 1.2379 0.06212 0.05701 0.0326 0.0364 1.0000
17.000 1.2347 0.06553 0.06049 0.0317 0.0358 1.0000
17.250 1.2307 0.06909 0.06411 0.0307 0.0352 1.0000
17.500 1.2255 0.07279 0.06787 0.0297 0.0347 1.0000
17.750 1.2188 0.07653 0.07165 0.0290 0.0339 1.0000
18.000 1.2166 0.08009 0.07532 0.0278 0.0336 1.0000
18.250 1.2140 0.08376 0.07911 0.0264 0.0332 1.0000
18.500 1.2106 0.08765 0.08311 0.0249 0.0327 1.0000
18.750 1.2067 0.09159 0.08716 0.0234 0.0322 1.0000
19.000 1.2030 0.09548 0.09114 0.0219 0.0318 1.0000
19.250 1.1989 0.09950 0.09524 0.0202 0.0313 1.0000
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