NACA 65(2)-215 (naca652215-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 65(2)-215 (naca652215-il) Reynolds number: 500,000 Max Cl/Cd: 82.49 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca652215-il-500000.txt Download as CSV file: xf-naca652215-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-215
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6834 0.07567 0.07293 -0.0608 1.0000 0.0238
-13.250 -0.7095 0.06919 0.06632 -0.0642 1.0000 0.0237
-13.000 -0.7338 0.06357 0.06057 -0.0664 1.0000 0.0235
-12.750 -0.7544 0.05876 0.05565 -0.0674 1.0000 0.0230
-12.500 -0.7799 0.05402 0.05072 -0.0677 1.0000 0.0229
-12.250 -0.8015 0.04993 0.04645 -0.0669 1.0000 0.0226
-12.000 -0.8245 0.04591 0.04220 -0.0652 1.0000 0.0223
-11.750 -0.8477 0.04199 0.03800 -0.0623 1.0000 0.0219
-11.500 -0.8609 0.03937 0.03518 -0.0591 1.0000 0.0220
-11.250 -0.8778 0.03670 0.03226 -0.0544 1.0000 0.0218
-11.000 -0.8702 0.03394 0.02923 -0.0539 0.9883 0.0220
-10.750 -0.8475 0.03119 0.02617 -0.0556 0.9783 0.0225
-10.500 -0.8206 0.02904 0.02374 -0.0575 0.9695 0.0231
-10.250 -0.7945 0.02748 0.02191 -0.0587 0.9583 0.0238
-10.000 -0.7735 0.02630 0.02049 -0.0584 0.9448 0.0241
-9.750 -0.7558 0.02517 0.01915 -0.0573 0.9319 0.0244
-9.500 -0.7276 0.02261 0.01646 -0.0580 0.9249 0.0250
-9.250 -0.7062 0.02157 0.01537 -0.0573 0.9146 0.0256
-9.000 -0.6862 0.02080 0.01453 -0.0564 0.9045 0.0262
-8.750 -0.6665 0.02018 0.01382 -0.0553 0.8955 0.0269
-8.500 -0.6460 0.01953 0.01311 -0.0544 0.8863 0.0277
-8.250 -0.6251 0.01886 0.01234 -0.0534 0.8786 0.0284
-8.000 -0.6042 0.01820 0.01161 -0.0525 0.8701 0.0290
-7.750 -0.5834 0.01771 0.01101 -0.0515 0.8628 0.0296
-7.500 -0.5643 0.01686 0.01010 -0.0503 0.8547 0.0302
-7.250 -0.5488 0.01593 0.00911 -0.0486 0.8477 0.0313
-7.000 -0.5295 0.01539 0.00856 -0.0476 0.8403 0.0324
-6.750 -0.5093 0.01494 0.00805 -0.0465 0.8339 0.0336
-6.500 -0.4881 0.01452 0.00759 -0.0456 0.8274 0.0350
-6.250 -0.4665 0.01412 0.00712 -0.0448 0.8208 0.0361
-6.000 -0.4477 0.01350 0.00641 -0.0435 0.8150 0.0378
-5.750 -0.4263 0.01301 0.00592 -0.0427 0.8085 0.0401
-5.500 -0.4029 0.01268 0.00553 -0.0422 0.8031 0.0429
-5.250 -0.3799 0.01229 0.00509 -0.0416 0.7980 0.0469
-5.000 -0.3560 0.01193 0.00473 -0.0411 0.7923 0.0532
-4.750 -0.3337 0.01140 0.00429 -0.0404 0.7872 0.0754
-4.500 -0.3180 0.01022 0.00371 -0.0392 0.7821 0.2064
-4.250 -0.3050 0.00864 0.00304 -0.0378 0.7764 0.4155
-4.000 -0.2833 0.00806 0.00290 -0.0371 0.7716 0.5376
-3.750 -0.2562 0.00801 0.00287 -0.0370 0.7675 0.5725
-3.500 -0.2283 0.00798 0.00285 -0.0371 0.7628 0.5932
-3.250 -0.2002 0.00798 0.00282 -0.0371 0.7583 0.6091
-3.000 -0.1721 0.00799 0.00280 -0.0372 0.7542 0.6215
-2.750 -0.1442 0.00807 0.00287 -0.0372 0.7500 0.6394
-2.500 -0.1166 0.00822 0.00303 -0.0371 0.7455 0.6598
-2.250 -0.0886 0.00831 0.00314 -0.0370 0.7414 0.6719
-2.000 -0.0600 0.00836 0.00311 -0.0372 0.7378 0.6790
-1.750 -0.0313 0.00836 0.00310 -0.0374 0.7339 0.6831
-1.500 -0.0026 0.00834 0.00308 -0.0377 0.7296 0.6868
-1.250 0.0264 0.00834 0.00302 -0.0380 0.7257 0.6906
-1.000 0.0555 0.00835 0.00297 -0.0384 0.7224 0.6942
-0.750 0.0842 0.00834 0.00296 -0.0387 0.7188 0.6974
-0.500 0.1129 0.00833 0.00297 -0.0390 0.7148 0.7007
-0.250 0.1418 0.00833 0.00296 -0.0393 0.7110 0.7044
0.000 0.1709 0.00836 0.00294 -0.0397 0.7077 0.7083
0.250 0.1999 0.00839 0.00295 -0.0401 0.7045 0.7118
0.500 0.2284 0.00838 0.00299 -0.0403 0.7008 0.7150
0.750 0.2572 0.00839 0.00303 -0.0406 0.6971 0.7188
1.000 0.2861 0.00842 0.00305 -0.0410 0.6937 0.7230
1.250 0.3152 0.00846 0.00307 -0.0414 0.6906 0.7269
1.500 0.3438 0.00849 0.00314 -0.0416 0.6873 0.7303
1.750 0.3723 0.00852 0.00323 -0.0419 0.6837 0.7342
2.000 0.4011 0.00855 0.00329 -0.0422 0.6801 0.7387
2.250 0.4300 0.00859 0.00333 -0.0426 0.6765 0.7430
2.500 0.4585 0.00863 0.00340 -0.0428 0.6723 0.7468
2.750 0.4863 0.00861 0.00346 -0.0428 0.6662 0.7510
3.000 0.5147 0.00861 0.00346 -0.0430 0.6599 0.7557
3.250 0.5421 0.00856 0.00344 -0.0429 0.6501 0.7603
3.500 0.5684 0.00846 0.00337 -0.0425 0.6354 0.7647
3.750 0.5947 0.00841 0.00332 -0.0422 0.6185 0.7697
4.000 0.6219 0.00843 0.00334 -0.0421 0.6052 0.7748
4.250 0.6484 0.00844 0.00340 -0.0418 0.5922 0.7792
4.500 0.6747 0.00849 0.00348 -0.0416 0.5758 0.7844
4.750 0.7003 0.00859 0.00357 -0.0413 0.5523 0.7902
5.000 0.7234 0.00877 0.00369 -0.0404 0.5130 0.7953
5.250 0.7378 0.00947 0.00399 -0.0382 0.4180 0.8013
5.500 0.7429 0.01088 0.00473 -0.0348 0.2851 0.8080
5.750 0.7484 0.01216 0.00548 -0.0316 0.1730 0.8142
6.000 0.7540 0.01340 0.00623 -0.0283 0.0833 0.8219
6.250 0.7665 0.01412 0.00682 -0.0260 0.0532 0.8287
6.500 0.7828 0.01465 0.00734 -0.0242 0.0446 0.8365
6.750 0.7945 0.01522 0.00794 -0.0216 0.0398 0.8442
7.000 0.8094 0.01560 0.00839 -0.0195 0.0374 0.8528
7.250 0.8219 0.01609 0.00894 -0.0171 0.0351 0.8613
7.500 0.8303 0.01683 0.00972 -0.0142 0.0331 0.8718
7.750 0.8407 0.01744 0.01043 -0.0116 0.0318 0.8828
8.000 0.8523 0.01799 0.01108 -0.0092 0.0306 0.8947
8.250 0.8628 0.01858 0.01175 -0.0068 0.0294 0.9088
8.500 0.8713 0.01923 0.01248 -0.0041 0.0286 0.9266
8.750 0.8808 0.01998 0.01331 -0.0018 0.0276 0.9526
9.000 0.8975 0.02152 0.01492 -0.0020 0.0265 1.0000
9.250 0.9157 0.02231 0.01575 -0.0015 0.0260 1.0000
9.500 0.9327 0.02318 0.01666 -0.0008 0.0254 1.0000
9.750 0.9492 0.02410 0.01763 0.0000 0.0248 1.0000
10.000 0.9658 0.02502 0.01858 0.0008 0.0242 1.0000
10.250 0.9823 0.02590 0.01949 0.0015 0.0234 1.0000
10.500 0.9985 0.02685 0.02045 0.0023 0.0228 1.0000
10.750 1.0153 0.02792 0.02153 0.0030 0.0223 1.0000
11.000 1.0367 0.02927 0.02288 0.0035 0.0217 1.0000
11.250 1.0621 0.03080 0.02451 0.0036 0.0213 1.0000
11.500 1.0790 0.03195 0.02577 0.0043 0.0211 1.0000
11.750 1.0947 0.03323 0.02717 0.0051 0.0208 1.0000
12.000 1.1105 0.03469 0.02878 0.0059 0.0205 1.0000
12.250 1.1239 0.03623 0.03047 0.0068 0.0202 1.0000
12.500 1.1349 0.03785 0.03223 0.0078 0.0198 1.0000
12.750 1.1437 0.03945 0.03396 0.0088 0.0194 1.0000
13.000 1.1517 0.04125 0.03590 0.0098 0.0191 1.0000
13.250 1.1575 0.04345 0.03827 0.0108 0.0189 1.0000
13.500 1.1631 0.04530 0.04021 0.0117 0.0186 1.0000
13.750 1.1667 0.04753 0.04257 0.0125 0.0184 1.0000
14.000 1.1684 0.04986 0.04502 0.0133 0.0182 1.0000
14.250 1.1656 0.05275 0.04809 0.0140 0.0181 1.0000
14.500 1.1627 0.05560 0.05107 0.0145 0.0180 1.0000
14.750 1.1552 0.05909 0.05474 0.0148 0.0179 1.0000
15.000 1.1407 0.06348 0.05936 0.0149 0.0180 1.0000
15.250 1.1258 0.06800 0.06409 0.0145 0.0179 1.0000
15.500 1.0178 0.08671 0.08369 0.0092 0.0192 1.0000
15.750 0.9774 0.09724 0.09448 0.0039 0.0196 1.0000
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