NACA 65(2)-415 a=0.5 (naca652415a05-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65(2)-415 a=0.5 (naca652415a05-il) Reynolds number: 200,000 Max Cl/Cd: 73.24 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca652415a05-il-200000-n5.txt Download as CSV file: xf-naca652415a05-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65(2)-415 a=0.5
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4002 0.09038 0.08647 -0.0634 0.8536 0.0221
-11.500 -0.4200 0.08119 0.07727 -0.0687 0.8470 0.0226
-11.250 -0.5232 0.05746 0.05320 -0.0841 0.8397 0.0210
-11.000 -0.5523 0.05237 0.04786 -0.0851 0.8310 0.0210
-10.750 -0.5595 0.05023 0.04558 -0.0845 0.8240 0.0213
-10.500 -0.5754 0.04733 0.04246 -0.0827 0.8163 0.0216
-10.250 -0.5905 0.04472 0.03959 -0.0796 0.8104 0.0218
-10.000 -0.5971 0.04187 0.03645 -0.0775 0.8040 0.0223
-9.750 -0.6006 0.03881 0.03299 -0.0752 0.7985 0.0228
-9.500 -0.6000 0.03571 0.02941 -0.0729 0.7940 0.0233
-9.250 -0.5936 0.03283 0.02602 -0.0711 0.7885 0.0240
-9.000 -0.5812 0.03067 0.02345 -0.0696 0.7835 0.0246
-8.750 -0.5623 0.02965 0.02234 -0.0690 0.7794 0.0253
-8.500 -0.5424 0.02871 0.02127 -0.0684 0.7752 0.0260
-8.250 -0.5218 0.02760 0.01999 -0.0678 0.7707 0.0270
-8.000 -0.5009 0.02624 0.01838 -0.0671 0.7667 0.0278
-7.750 -0.4790 0.02496 0.01681 -0.0665 0.7633 0.0286
-7.500 -0.4559 0.02397 0.01552 -0.0659 0.7599 0.0296
-7.250 -0.4322 0.02286 0.01439 -0.0657 0.7557 0.0306
-7.000 -0.4082 0.02210 0.01357 -0.0654 0.7517 0.0316
-6.750 -0.3840 0.02132 0.01268 -0.0651 0.7482 0.0326
-6.500 -0.3597 0.02055 0.01179 -0.0646 0.7454 0.0336
-6.250 -0.3350 0.01986 0.01102 -0.0644 0.7415 0.0347
-6.000 -0.3101 0.01934 0.01039 -0.0640 0.7379 0.0360
-5.750 -0.2872 0.01852 0.00958 -0.0635 0.7347 0.0374
-5.500 -0.2636 0.01795 0.00898 -0.0631 0.7318 0.0386
-5.250 -0.2399 0.01744 0.00841 -0.0625 0.7294 0.0400
-5.000 -0.2159 0.01698 0.00791 -0.0622 0.7259 0.0416
-4.750 -0.1912 0.01661 0.00748 -0.0618 0.7223 0.0437
-4.500 -0.1679 0.01610 0.00697 -0.0614 0.7191 0.0463
-4.250 -0.1432 0.01575 0.00655 -0.0610 0.7163 0.0492
-4.000 -0.1179 0.01544 0.00616 -0.0607 0.7141 0.0526
-3.750 -0.0931 0.01510 0.00582 -0.0604 0.7114 0.0585
-3.500 -0.0679 0.01478 0.00554 -0.0602 0.7084 0.0696
-3.250 -0.0436 0.01436 0.00526 -0.0600 0.7055 0.1013
-3.000 -0.0228 0.01353 0.00493 -0.0594 0.7027 0.2195
-2.750 -0.0065 0.01235 0.00463 -0.0581 0.7001 0.4379
-2.500 0.0158 0.01197 0.00463 -0.0571 0.6979 0.5557
-2.250 0.0408 0.01187 0.00469 -0.0566 0.6954 0.6129
-2.000 0.0645 0.01186 0.00491 -0.0555 0.6926 0.6759
-1.750 0.0883 0.01197 0.00514 -0.0543 0.6900 0.7235
-1.500 0.1145 0.01204 0.00522 -0.0538 0.6876 0.7435
-1.250 0.1422 0.01205 0.00516 -0.0539 0.6852 0.7534
-1.000 0.1701 0.01206 0.00512 -0.0539 0.6831 0.7598
-0.750 0.1982 0.01208 0.00506 -0.0540 0.6812 0.7675
-0.500 0.2254 0.01214 0.00513 -0.0540 0.6787 0.7745
-0.250 0.2526 0.01221 0.00520 -0.0541 0.6761 0.7820
0.000 0.2800 0.01226 0.00524 -0.0541 0.6735 0.7894
0.250 0.3073 0.01231 0.00528 -0.0541 0.6710 0.7967
0.500 0.3350 0.01235 0.00529 -0.0542 0.6689 0.8050
0.750 0.3626 0.01240 0.00534 -0.0542 0.6671 0.8118
1.000 0.3906 0.01246 0.00537 -0.0543 0.6655 0.8204
1.250 0.4165 0.01258 0.00555 -0.0541 0.6627 0.8277
1.500 0.4428 0.01269 0.00570 -0.0540 0.6598 0.8366
1.750 0.4692 0.01278 0.00584 -0.0539 0.6573 0.8439
2.000 0.4960 0.01287 0.00595 -0.0538 0.6551 0.8531
2.250 0.5229 0.01294 0.00605 -0.0537 0.6530 0.8607
2.500 0.5503 0.01301 0.00613 -0.0537 0.6511 0.8700
2.750 0.5775 0.01309 0.00625 -0.0536 0.6492 0.8779
3.000 0.6018 0.01328 0.00653 -0.0532 0.6461 0.8880
3.250 0.6273 0.01342 0.00676 -0.0529 0.6431 0.8970
3.500 0.6537 0.01354 0.00694 -0.0528 0.6404 0.9067
3.750 0.6812 0.01362 0.00708 -0.0529 0.6380 0.9168
4.000 0.7110 0.01368 0.00719 -0.0533 0.6358 0.9256
4.250 0.7405 0.01376 0.00731 -0.0538 0.6334 0.9356
4.500 0.7687 0.01396 0.00765 -0.0544 0.6286 0.9457
4.750 0.8007 0.01404 0.00782 -0.0555 0.6243 0.9546
5.000 0.8352 0.01398 0.00781 -0.0569 0.6202 0.9631
5.250 0.8689 0.01403 0.00797 -0.0585 0.6131 0.9717
5.500 0.9045 0.01396 0.00797 -0.0602 0.6059 0.9798
5.750 0.9389 0.01365 0.00769 -0.0616 0.5893 0.9895
6.000 0.9649 0.01342 0.00747 -0.0615 0.5607 1.0000
6.250 0.9783 0.01344 0.00747 -0.0590 0.5368 1.0000
6.500 0.9939 0.01357 0.00755 -0.0569 0.5087 1.0000
6.750 1.0048 0.01386 0.00762 -0.0540 0.4583 1.0000
7.000 1.0006 0.01477 0.00808 -0.0490 0.3887 1.0000
7.250 0.9875 0.01596 0.00892 -0.0428 0.3335 1.0000
7.500 0.9744 0.01745 0.01012 -0.0373 0.2830 1.0000
7.750 0.9647 0.01916 0.01154 -0.0331 0.2329 1.0000
8.000 0.9590 0.02091 0.01303 -0.0297 0.1871 1.0000
8.250 0.9546 0.02275 0.01460 -0.0268 0.1413 1.0000
8.500 0.9537 0.02450 0.01613 -0.0244 0.1047 1.0000
8.750 0.9560 0.02613 0.01759 -0.0224 0.0772 1.0000
9.000 0.9611 0.02764 0.01898 -0.0208 0.0592 1.0000
9.250 0.9686 0.02902 0.02033 -0.0194 0.0494 1.0000
9.500 0.9772 0.03036 0.02167 -0.0181 0.0429 1.0000
9.750 0.9855 0.03175 0.02306 -0.0169 0.0386 1.0000
10.000 0.9951 0.03307 0.02443 -0.0158 0.0353 1.0000
10.250 1.0022 0.03461 0.02597 -0.0147 0.0327 1.0000
10.500 1.0120 0.03597 0.02742 -0.0137 0.0308 1.0000
10.750 1.0209 0.03742 0.02894 -0.0127 0.0293 1.0000
11.000 1.0293 0.03897 0.03054 -0.0118 0.0283 1.0000
11.250 1.0357 0.04070 0.03230 -0.0109 0.0271 1.0000
11.500 1.0425 0.04245 0.03411 -0.0100 0.0263 1.0000
11.750 1.0525 0.04396 0.03571 -0.0093 0.0252 1.0000
12.000 1.0610 0.04562 0.03744 -0.0086 0.0244 1.0000
12.250 1.0700 0.04726 0.03914 -0.0080 0.0236 1.0000
12.500 1.0787 0.04896 0.04088 -0.0074 0.0228 1.0000
12.750 1.0872 0.05070 0.04266 -0.0069 0.0223 1.0000
13.000 1.0946 0.05256 0.04455 -0.0062 0.0216 1.0000
13.250 1.1051 0.05418 0.04626 -0.0056 0.0213 1.0000
13.500 1.1158 0.05581 0.04799 -0.0051 0.0209 1.0000
13.750 1.1264 0.05748 0.04977 -0.0046 0.0205 1.0000
14.000 1.1373 0.05916 0.05155 -0.0041 0.0201 1.0000
14.250 1.1477 0.06093 0.05343 -0.0037 0.0197 1.0000
14.500 1.1574 0.06279 0.05541 -0.0033 0.0193 1.0000
14.750 1.1663 0.06478 0.05750 -0.0030 0.0189 1.0000
15.000 1.1748 0.06684 0.05967 -0.0028 0.0186 1.0000
15.250 1.1823 0.06904 0.06196 -0.0027 0.0183 1.0000
15.500 1.1891 0.07132 0.06432 -0.0027 0.0180 1.0000
15.750 1.1958 0.07363 0.06668 -0.0027 0.0177 1.0000
16.000 1.1981 0.07663 0.06987 -0.0028 0.0174 1.0000
16.250 1.1982 0.07995 0.07342 -0.0032 0.0172 1.0000
16.500 1.1958 0.08364 0.07735 -0.0038 0.0170 1.0000
16.750 1.1920 0.08765 0.08158 -0.0045 0.0168 1.0000
17.000 1.1861 0.09203 0.08619 -0.0056 0.0167 1.0000
17.250 1.1779 0.09687 0.09126 -0.0071 0.0166 1.0000
17.500 1.1674 0.10223 0.09686 -0.0089 0.0165 1.0000
17.750 1.1550 0.10809 0.10295 -0.0113 0.0164 1.0000
18.000 1.1401 0.11463 0.10972 -0.0143 0.0163 1.0000
18.250 1.1239 0.12168 0.11700 -0.0179 0.0164 1.0000
18.500 1.1042 0.12986 0.12542 -0.0224 0.0163 1.0000
18.750 1.0813 0.13928 0.13506 -0.0280 0.0164 1.0000
19.000 1.0532 0.15068 0.14670 -0.0352 0.0165 1.0000
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Polar data table (+)
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