NACA 6-H-15 AIRFOIL (n6h15-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 6-H-15 AIRFOIL (n6h15-il) Reynolds number: 500,000 Max Cl/Cd: 85.13 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n6h15-il-500000.txt Download as CSV file: xf-n6h15-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 6-H-15 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3597 0.08896 0.08550 -0.0298 0.6310 0.0246
-9.500 -0.3656 0.08456 0.08113 -0.0327 0.6295 0.0247
-9.250 -0.3759 0.08007 0.07665 -0.0358 0.6278 0.0251
-9.000 -0.3898 0.07584 0.07239 -0.0373 0.6263 0.0252
-8.750 -0.4039 0.07221 0.06873 -0.0371 0.6248 0.0254
-8.500 -0.4188 0.06898 0.06545 -0.0352 0.6233 0.0258
-8.250 -0.4292 0.06568 0.06205 -0.0333 0.6218 0.0261
-8.000 -0.4505 0.05848 0.05447 -0.0301 0.6207 0.0279
-7.750 -0.4557 0.05396 0.04970 -0.0269 0.6194 0.0280
-7.500 -0.4644 0.04861 0.04422 -0.0241 0.6179 0.0284
-7.250 -0.4540 0.04668 0.04225 -0.0227 0.6160 0.0287
-7.000 -0.4400 0.04549 0.04102 -0.0217 0.6139 0.0292
-6.750 -0.4262 0.04391 0.03935 -0.0204 0.6119 0.0299
-6.500 -0.4480 0.03247 0.02684 -0.0112 0.6110 0.0286
-6.250 -0.4304 0.02999 0.02420 -0.0096 0.6093 0.0270
-6.000 -0.4180 0.02630 0.01998 -0.0066 0.6079 0.0271
-5.750 -0.3985 0.02502 0.01822 -0.0046 0.6062 0.0280
-5.500 -0.3767 0.02268 0.01577 -0.0042 0.6045 0.0294
-5.250 -0.3515 0.02211 0.01519 -0.0039 0.6029 0.0305
-5.000 -0.3255 0.02080 0.01368 -0.0035 0.6012 0.0313
-4.750 -0.2981 0.01966 0.01234 -0.0033 0.5994 0.0324
-4.500 -0.2709 0.01906 0.01155 -0.0031 0.5977 0.0335
-4.250 -0.2403 0.01760 0.00993 -0.0037 0.5960 0.0350
-4.000 -0.2104 0.01678 0.00909 -0.0043 0.5945 0.0361
-3.750 -0.1812 0.01622 0.00847 -0.0046 0.5930 0.0371
-3.500 -0.1523 0.01576 0.00796 -0.0049 0.5916 0.0386
-3.250 -0.1237 0.01541 0.00754 -0.0051 0.5902 0.0400
-3.000 -0.0951 0.01505 0.00713 -0.0053 0.5887 0.0409
-2.750 -0.0664 0.01444 0.00651 -0.0056 0.5873 0.0418
-2.500 -0.0399 0.01383 0.00593 -0.0055 0.5855 0.0437
-2.250 -0.0139 0.01353 0.00564 -0.0052 0.5837 0.0454
-2.000 0.0118 0.01325 0.00536 -0.0049 0.5819 0.0470
-1.750 0.0374 0.01302 0.00510 -0.0045 0.5803 0.0486
-1.500 0.0631 0.01284 0.00489 -0.0041 0.5788 0.0502
-1.250 0.0875 0.01255 0.00460 -0.0035 0.5775 0.0541
-1.000 0.1129 0.01241 0.00445 -0.0031 0.5762 0.0584
-0.750 0.1377 0.01230 0.00434 -0.0026 0.5747 0.0678
-0.500 0.1601 0.01201 0.00432 -0.0018 0.5735 0.1329
-0.250 0.1664 0.01101 0.00424 0.0020 0.5723 0.4008
0.250 0.1609 0.00994 0.00477 0.0154 0.5699 0.8726
0.500 0.1866 0.01036 0.00518 0.0163 0.5686 0.8899
0.750 0.2251 0.01100 0.00584 0.0148 0.5674 0.9041
1.000 0.3389 0.01289 0.00768 -0.0014 0.5661 0.9213
1.250 0.4528 0.01426 0.00897 -0.0180 0.5648 0.9377
1.500 0.5286 0.01427 0.00890 -0.0277 0.5633 0.9443
1.750 0.5644 0.01428 0.00888 -0.0295 0.5620 0.9476
2.000 0.5892 0.01445 0.00902 -0.0291 0.5607 0.9519
2.250 0.6192 0.01454 0.00908 -0.0298 0.5594 0.9559
2.500 0.6284 0.01471 0.00928 -0.0265 0.5583 0.9549
2.750 0.6492 0.01465 0.00926 -0.0255 0.5562 0.9548
3.000 0.6696 0.01461 0.00925 -0.0244 0.5541 0.9540
3.250 0.6979 0.01442 0.00907 -0.0249 0.5518 0.9534
3.500 0.7241 0.01424 0.00888 -0.0249 0.5495 0.9530
3.750 0.7492 0.01406 0.00868 -0.0246 0.5471 0.9526
4.000 0.7737 0.01397 0.00855 -0.0243 0.5448 0.9522
4.250 0.7965 0.01388 0.00851 -0.0237 0.5420 0.9520
4.500 0.8184 0.01380 0.00850 -0.0229 0.5393 0.9521
4.750 0.8398 0.01369 0.00841 -0.0220 0.5361 0.9522
5.000 0.8625 0.01349 0.00821 -0.0212 0.5326 0.9521
5.250 0.8850 0.01339 0.00808 -0.0205 0.5297 0.9519
5.500 0.9056 0.01334 0.00810 -0.0195 0.5269 0.9519
5.750 0.9253 0.01324 0.00808 -0.0183 0.5231 0.9520
6.000 0.9446 0.01311 0.00797 -0.0169 0.5190 0.9522
6.250 0.9640 0.01299 0.00783 -0.0155 0.5150 0.9524
6.500 0.9770 0.01294 0.00787 -0.0130 0.5107 0.9532
6.750 0.9811 0.01284 0.00784 -0.0085 0.5054 0.9544
7.000 1.0043 0.01269 0.00767 -0.0080 0.4991 0.9546
7.250 1.0269 0.01261 0.00771 -0.0075 0.4901 0.9550
7.500 1.0495 0.01256 0.00770 -0.0070 0.4794 0.9554
7.750 1.0709 0.01258 0.00774 -0.0063 0.4606 0.9559
8.000 1.0812 0.01311 0.00806 -0.0042 0.4005 0.9570
8.250 1.0594 0.01487 0.00948 0.0022 0.3403 0.9603
8.500 1.0278 0.01574 0.01036 0.0112 0.3303 0.9663
8.750 1.0035 0.01753 0.01212 0.0167 0.3131 0.9711
9.000 0.9883 0.02114 0.01552 0.0173 0.2526 0.9743
9.250 0.9627 0.02505 0.01917 0.0195 0.2036 0.9786
9.500 0.9425 0.02816 0.02211 0.0222 0.1665 0.9829
9.750 0.9297 0.03198 0.02559 0.0220 0.1058 0.9846
10.000 0.9347 0.03425 0.02777 0.0216 0.0895 0.9860
10.250 0.9443 0.03616 0.02967 0.0211 0.0832 0.9875
10.500 0.9583 0.03765 0.03121 0.0205 0.0803 0.9891
10.750 0.9716 0.03918 0.03279 0.0200 0.0782 0.9908
11.000 0.9824 0.04086 0.03451 0.0198 0.0761 0.9926
11.250 0.9926 0.04267 0.03633 0.0194 0.0733 0.9943
11.500 1.0001 0.04495 0.03865 0.0187 0.0701 0.9960
11.750 1.0172 0.04634 0.04010 0.0178 0.0689 0.9975
12.000 1.0335 0.04785 0.04167 0.0168 0.0675 0.9987
12.250 1.0490 0.04951 0.04338 0.0157 0.0656 0.9997
12.500 1.0430 0.05039 0.04430 0.0193 0.0648 1.0000
12.750 1.0364 0.05120 0.04511 0.0232 0.0634 1.0000
13.000 1.0387 0.05264 0.04656 0.0248 0.0617 1.0000
13.250 1.0412 0.05433 0.04826 0.0260 0.0601 1.0000
13.500 1.0431 0.05610 0.05006 0.0272 0.0584 1.0000
13.750 1.0544 0.05728 0.05129 0.0277 0.0574 1.0000
14.000 1.0646 0.05861 0.05268 0.0281 0.0562 1.0000
14.250 1.0739 0.06002 0.05415 0.0285 0.0549 1.0000
14.500 1.0840 0.06143 0.05560 0.0287 0.0530 1.0000
14.750 1.0929 0.06296 0.05716 0.0290 0.0510 1.0000
15.000 1.0974 0.06489 0.05908 0.0294 0.0489 1.0000
15.250 1.1062 0.06648 0.06073 0.0296 0.0472 1.0000
15.500 1.1187 0.06782 0.06216 0.0295 0.0450 1.0000
15.750 1.1300 0.06928 0.06365 0.0293 0.0420 1.0000
16.000 1.1373 0.07115 0.06551 0.0293 0.0387 1.0000
16.250 1.1503 0.07243 0.06682 0.0291 0.0339 1.0000
16.500 1.1583 0.07421 0.06858 0.0291 0.0290 1.0000
16.750 1.1624 0.07646 0.07082 0.0291 0.0257 1.0000
17.000 1.1661 0.07876 0.07314 0.0291 0.0231 1.0000
17.250 1.1676 0.08132 0.07570 0.0290 0.0215 1.0000
17.500 1.1703 0.08378 0.07824 0.0289 0.0203 1.0000
17.750 1.1725 0.08630 0.08082 0.0288 0.0193 1.0000
18.000 1.1712 0.08933 0.08386 0.0285 0.0180 1.0000
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