NACA 64-215 AIRFOIL (n64215-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-215 AIRFOIL (n64215-il) Reynolds number: 200,000 Max Cl/Cd: 58.89 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64215-il-200000-n5.txt Download as CSV file: xf-n64215-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-215 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.8021 0.08024 0.07576 -0.0456 1.0000 0.0222
-14.500 -0.8305 0.07235 0.06763 -0.0503 1.0000 0.0222
-14.250 -0.8542 0.06593 0.06098 -0.0536 1.0000 0.0222
-14.000 -0.8693 0.06114 0.05599 -0.0557 1.0000 0.0223
-13.750 -0.8813 0.05698 0.05164 -0.0571 1.0000 0.0225
-13.500 -0.8889 0.05358 0.04808 -0.0579 1.0000 0.0228
-13.250 -0.8966 0.05024 0.04455 -0.0584 1.0000 0.0230
-13.000 -0.9020 0.04723 0.04133 -0.0584 1.0000 0.0233
-12.750 -0.9049 0.04452 0.03842 -0.0581 1.0000 0.0235
-12.500 -0.9056 0.04202 0.03570 -0.0576 1.0000 0.0238
-12.250 -0.9038 0.03978 0.03325 -0.0568 1.0000 0.0242
-12.000 -0.8994 0.03777 0.03102 -0.0559 1.0000 0.0245
-11.750 -0.8924 0.03594 0.02897 -0.0549 1.0000 0.0249
-11.500 -0.8836 0.03430 0.02712 -0.0539 1.0000 0.0253
-11.250 -0.8706 0.03289 0.02570 -0.0531 1.0000 0.0258
-11.000 -0.8583 0.03175 0.02454 -0.0522 1.0000 0.0263
-10.750 -0.8462 0.03067 0.02341 -0.0511 1.0000 0.0268
-10.500 -0.8341 0.02967 0.02234 -0.0499 1.0000 0.0275
-10.250 -0.8213 0.02863 0.02122 -0.0485 1.0000 0.0283
-10.000 -0.8087 0.02764 0.02015 -0.0470 1.0000 0.0289
-9.750 -0.7978 0.02675 0.01918 -0.0450 1.0000 0.0295
-9.500 -0.7697 0.02564 0.01793 -0.0462 0.9816 0.0304
-9.250 -0.7406 0.02436 0.01666 -0.0480 0.9652 0.0313
-9.000 -0.7117 0.02337 0.01564 -0.0495 0.9504 0.0325
-8.750 -0.6849 0.02252 0.01472 -0.0504 0.9358 0.0340
-8.500 -0.6615 0.02177 0.01386 -0.0505 0.9213 0.0357
-8.250 -0.6420 0.02100 0.01300 -0.0498 0.9072 0.0371
-8.000 -0.6239 0.02027 0.01223 -0.0489 0.8941 0.0386
-7.750 -0.6050 0.01965 0.01155 -0.0479 0.8825 0.0403
-7.500 -0.5863 0.01909 0.01090 -0.0467 0.8707 0.0424
-7.250 -0.5678 0.01850 0.01024 -0.0456 0.8602 0.0448
-7.000 -0.5488 0.01794 0.00963 -0.0445 0.8505 0.0477
-6.750 -0.5282 0.01746 0.00907 -0.0436 0.8406 0.0510
-6.500 -0.5080 0.01692 0.00848 -0.0426 0.8322 0.0553
-6.250 -0.4861 0.01647 0.00797 -0.0420 0.8228 0.0614
-6.000 -0.4647 0.01596 0.00745 -0.0412 0.8151 0.0702
-5.750 -0.4425 0.01545 0.00698 -0.0406 0.8062 0.0846
-5.500 -0.4210 0.01487 0.00647 -0.0399 0.7990 0.1106
-5.250 -0.3997 0.01419 0.00600 -0.0394 0.7906 0.1548
-5.000 -0.3798 0.01334 0.00545 -0.0387 0.7833 0.2285
-4.750 -0.3611 0.01231 0.00493 -0.0380 0.7753 0.3409
-4.500 -0.3391 0.01178 0.00479 -0.0373 0.7682 0.4443
-4.250 -0.3130 0.01165 0.00471 -0.0371 0.7616 0.4845
-4.000 -0.2861 0.01159 0.00464 -0.0368 0.7545 0.5125
-3.750 -0.2592 0.01158 0.00458 -0.0366 0.7486 0.5378
-3.500 -0.2321 0.01158 0.00459 -0.0364 0.7412 0.5589
-3.250 -0.2051 0.01163 0.00463 -0.0360 0.7347 0.5794
-3.000 -0.1779 0.01170 0.00468 -0.0357 0.7283 0.5965
-2.750 -0.1498 0.01169 0.00458 -0.0358 0.7216 0.6060
-2.500 -0.1218 0.01165 0.00448 -0.0358 0.7161 0.6104
-2.250 -0.0935 0.01162 0.00441 -0.0359 0.7099 0.6162
-2.000 -0.0651 0.01160 0.00430 -0.0361 0.7039 0.6225
-1.750 -0.0370 0.01157 0.00423 -0.0360 0.6990 0.6265
-1.500 -0.0086 0.01155 0.00419 -0.0362 0.6929 0.6310
-1.250 0.0198 0.01153 0.00411 -0.0364 0.6871 0.6361
-1.000 0.0482 0.01152 0.00402 -0.0365 0.6822 0.6404
-0.750 0.0765 0.01150 0.00402 -0.0366 0.6761 0.6443
-0.500 0.1049 0.01150 0.00400 -0.0368 0.6708 0.6490
-0.250 0.1335 0.01152 0.00395 -0.0370 0.6664 0.6547
0.000 0.1617 0.01152 0.00399 -0.0371 0.6614 0.6591
0.250 0.1899 0.01154 0.00403 -0.0372 0.6563 0.6639
0.500 0.2185 0.01157 0.00403 -0.0374 0.6519 0.6694
0.750 0.2469 0.01161 0.00405 -0.0375 0.6478 0.6744
1.000 0.2749 0.01163 0.00415 -0.0376 0.6424 0.6792
1.250 0.3032 0.01168 0.00420 -0.0378 0.6377 0.6850
1.500 0.3317 0.01173 0.00426 -0.0379 0.6340 0.6909
1.750 0.3597 0.01179 0.00438 -0.0380 0.6300 0.6965
2.000 0.3879 0.01186 0.00450 -0.0381 0.6253 0.7031
2.250 0.4160 0.01192 0.00461 -0.0382 0.6209 0.7090
2.500 0.4440 0.01199 0.00471 -0.0382 0.6170 0.7148
2.750 0.4719 0.01207 0.00485 -0.0383 0.6112 0.7217
3.000 0.4995 0.01213 0.00499 -0.0383 0.6055 0.7275
3.250 0.5274 0.01221 0.00511 -0.0383 0.6012 0.7341
3.500 0.5551 0.01230 0.00529 -0.0383 0.5961 0.7414
3.750 0.5819 0.01235 0.00544 -0.0381 0.5881 0.7480
4.000 0.6087 0.01237 0.00550 -0.0378 0.5763 0.7561
4.250 0.6342 0.01237 0.00554 -0.0373 0.5610 0.7628
4.500 0.6601 0.01241 0.00561 -0.0368 0.5454 0.7705
4.750 0.6853 0.01245 0.00569 -0.0362 0.5267 0.7777
5.000 0.7095 0.01254 0.00576 -0.0355 0.5034 0.7855
5.250 0.7337 0.01266 0.00592 -0.0348 0.4771 0.7936
5.500 0.7568 0.01285 0.00610 -0.0339 0.4452 0.8021
5.750 0.7751 0.01329 0.00630 -0.0324 0.3775 0.8108
6.000 0.7863 0.01425 0.00683 -0.0300 0.2937 0.8205
6.250 0.7961 0.01531 0.00756 -0.0275 0.2216 0.8302
6.500 0.8079 0.01626 0.00825 -0.0254 0.1668 0.8412
6.750 0.8198 0.01709 0.00891 -0.0232 0.1275 0.8523
7.000 0.8317 0.01784 0.00955 -0.0210 0.0996 0.8645
7.250 0.8440 0.01851 0.01019 -0.0187 0.0806 0.8782
7.500 0.8555 0.01915 0.01081 -0.0164 0.0683 0.8941
7.750 0.8650 0.01971 0.01141 -0.0136 0.0603 0.9148
8.000 0.8770 0.02039 0.01212 -0.0116 0.0540 0.9444
8.250 0.8964 0.02115 0.01293 -0.0114 0.0488 1.0000
8.500 0.9095 0.02207 0.01384 -0.0102 0.0453 1.0000
8.750 0.9238 0.02293 0.01475 -0.0092 0.0422 1.0000
9.000 0.9355 0.02398 0.01579 -0.0080 0.0396 1.0000
9.250 0.9474 0.02505 0.01689 -0.0069 0.0378 1.0000
9.500 0.9601 0.02610 0.01801 -0.0059 0.0358 1.0000
9.750 0.9720 0.02724 0.01918 -0.0050 0.0341 1.0000
10.000 0.9814 0.02858 0.02052 -0.0040 0.0325 1.0000
10.250 0.9926 0.02985 0.02185 -0.0031 0.0314 1.0000
10.500 1.0042 0.03113 0.02321 -0.0022 0.0303 1.0000
10.750 1.0152 0.03248 0.02462 -0.0014 0.0293 1.0000
11.000 1.0261 0.03387 0.02605 -0.0007 0.0284 1.0000
11.250 1.0365 0.03532 0.02754 0.0000 0.0277 1.0000
11.500 1.0458 0.03693 0.02915 0.0007 0.0269 1.0000
11.750 1.0571 0.03843 0.03073 0.0014 0.0263 1.0000
12.000 1.0686 0.03992 0.03234 0.0020 0.0254 1.0000
12.250 1.0798 0.04147 0.03399 0.0025 0.0246 1.0000
12.500 1.0904 0.04306 0.03566 0.0029 0.0240 1.0000
12.750 1.1001 0.04474 0.03741 0.0033 0.0234 1.0000
13.000 1.1096 0.04650 0.03922 0.0037 0.0229 1.0000
13.250 1.1187 0.04832 0.04110 0.0040 0.0225 1.0000
13.500 1.1281 0.05023 0.04305 0.0043 0.0222 1.0000
13.750 1.1365 0.05230 0.04525 0.0046 0.0218 1.0000
14.000 1.1423 0.05467 0.04782 0.0048 0.0214 1.0000
14.250 1.1477 0.05712 0.05045 0.0049 0.0212 1.0000
14.500 1.1508 0.05985 0.05336 0.0048 0.0209 1.0000
14.750 1.1516 0.06290 0.05660 0.0045 0.0206 1.0000
15.000 1.1507 0.06622 0.06011 0.0040 0.0203 1.0000
15.250 1.1482 0.06982 0.06391 0.0033 0.0201 1.0000
15.500 1.1436 0.07378 0.06807 0.0022 0.0199 1.0000
15.750 1.1372 0.07811 0.07259 0.0008 0.0198 1.0000
16.000 1.1288 0.08289 0.07757 -0.0010 0.0196 1.0000
16.250 1.1186 0.08811 0.08298 -0.0032 0.0195 1.0000
16.500 1.1053 0.09411 0.08920 -0.0061 0.0194 1.0000
16.750 1.0918 0.10041 0.09569 -0.0094 0.0193 1.0000
17.000 1.0726 0.10814 0.10364 -0.0137 0.0192 1.0000
17.250 1.0466 0.11788 0.11364 -0.0197 0.0192 1.0000
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