NACA 5-H-15 AIRFOIL (n5h15-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 5-H-15 AIRFOIL (n5h15-il) Reynolds number: 200,000 Max Cl/Cd: 58.58 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n5h15-il-200000-n5.txt Download as CSV file: xf-n5h15-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 5-H-15 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4432 0.09096 0.08675 -0.0391 0.7433 0.0325
-10.750 -0.4590 0.08357 0.07939 -0.0438 0.7411 0.0323
-10.500 -0.4947 0.07315 0.06893 -0.0514 0.7390 0.0318
-10.250 -0.5283 0.06667 0.06231 -0.0527 0.7369 0.0317
-10.000 -0.5560 0.06209 0.05757 -0.0511 0.7347 0.0317
-9.750 -0.5795 0.05825 0.05358 -0.0480 0.7315 0.0318
-9.500 -0.5976 0.05531 0.05046 -0.0440 0.7284 0.0322
-9.250 -0.6105 0.05212 0.04703 -0.0403 0.7257 0.0328
-9.000 -0.6190 0.04883 0.04343 -0.0367 0.7232 0.0333
-8.750 -0.6233 0.04562 0.03988 -0.0332 0.7210 0.0338
-8.500 -0.6229 0.04262 0.03652 -0.0300 0.7186 0.0341
-8.250 -0.6183 0.03985 0.03340 -0.0271 0.7156 0.0344
-8.000 -0.6101 0.03751 0.03066 -0.0245 0.7128 0.0350
-7.750 -0.5985 0.03589 0.02864 -0.0221 0.7103 0.0357
-7.500 -0.5853 0.03347 0.02592 -0.0203 0.7082 0.0361
-7.250 -0.5679 0.03159 0.02380 -0.0190 0.7061 0.0364
-7.000 -0.5482 0.03006 0.02205 -0.0179 0.7040 0.0368
-6.750 -0.5265 0.02873 0.02056 -0.0173 0.7004 0.0372
-6.500 -0.5038 0.02751 0.01916 -0.0167 0.6969 0.0376
-6.250 -0.4803 0.02639 0.01787 -0.0161 0.6936 0.0380
-6.000 -0.4562 0.02545 0.01676 -0.0156 0.6908 0.0387
-5.750 -0.4314 0.02462 0.01578 -0.0152 0.6886 0.0396
-5.500 -0.4051 0.02375 0.01480 -0.0152 0.6851 0.0403
-5.250 -0.3778 0.02283 0.01375 -0.0153 0.6817 0.0408
-5.000 -0.3501 0.02195 0.01274 -0.0153 0.6786 0.0414
-4.750 -0.3223 0.02113 0.01179 -0.0154 0.6757 0.0419
-4.500 -0.2947 0.02039 0.01094 -0.0154 0.6732 0.0425
-4.250 -0.2668 0.01975 0.01027 -0.0156 0.6689 0.0431
-4.000 -0.2398 0.01916 0.00963 -0.0156 0.6651 0.0437
-3.750 -0.2135 0.01863 0.00904 -0.0155 0.6622 0.0443
-3.500 -0.1879 0.01811 0.00847 -0.0151 0.6598 0.0452
-3.250 -0.1640 0.01749 0.00786 -0.0146 0.6577 0.0469
-3.000 -0.1397 0.01713 0.00754 -0.0142 0.6543 0.0484
-2.750 -0.1157 0.01679 0.00720 -0.0137 0.6510 0.0498
-2.500 -0.0921 0.01645 0.00684 -0.0130 0.6480 0.0512
-2.250 -0.0683 0.01615 0.00648 -0.0123 0.6453 0.0528
-2.000 -0.0443 0.01588 0.00613 -0.0116 0.6429 0.0547
-1.750 -0.0205 0.01564 0.00589 -0.0110 0.6393 0.0574
-1.500 0.0034 0.01540 0.00566 -0.0104 0.6354 0.0621
-1.250 0.0278 0.01520 0.00543 -0.0099 0.6320 0.0690
-1.000 0.0504 0.01483 0.00515 -0.0090 0.6289 0.0914
-0.750 0.0533 0.01335 0.00483 -0.0048 0.6263 0.3842
-0.500 0.0892 0.01267 0.00595 -0.0050 0.6221 0.8495
-0.250 0.1220 0.01311 0.00634 -0.0053 0.6182 0.8713
0.000 0.1605 0.01376 0.00692 -0.0065 0.6147 0.8940
0.250 0.2539 0.01505 0.00806 -0.0179 0.6115 0.9161
0.500 0.2915 0.01518 0.00817 -0.0200 0.6066 0.9203
0.750 0.3168 0.01516 0.00812 -0.0198 0.6021 0.9241
1.250 0.3649 0.01503 0.00786 -0.0187 0.5946 0.9294
1.500 0.3955 0.01502 0.00786 -0.0197 0.5892 0.9307
1.750 0.4258 0.01498 0.00778 -0.0205 0.5846 0.9322
2.000 0.4547 0.01492 0.00765 -0.0209 0.5809 0.9338
2.250 0.4820 0.01494 0.00771 -0.0212 0.5750 0.9357
2.500 0.5082 0.01492 0.00769 -0.0212 0.5699 0.9379
2.750 0.5319 0.01488 0.00761 -0.0206 0.5659 0.9405
3.000 0.5480 0.01494 0.00770 -0.0186 0.5598 0.9440
3.250 0.5788 0.01492 0.00769 -0.0196 0.5544 0.9450
3.500 0.6085 0.01490 0.00766 -0.0203 0.5499 0.9461
3.750 0.6377 0.01496 0.00777 -0.0210 0.5437 0.9474
4.000 0.6666 0.01499 0.00780 -0.0216 0.5389 0.9489
4.250 0.6939 0.01502 0.00785 -0.0218 0.5347 0.9504
4.500 0.7196 0.01511 0.00800 -0.0219 0.5294 0.9520
4.750 0.7447 0.01518 0.00809 -0.0217 0.5250 0.9541
5.000 0.7677 0.01524 0.00817 -0.0210 0.5216 0.9563
5.250 0.7852 0.01538 0.00838 -0.0194 0.5173 0.9588
5.500 0.8138 0.01547 0.00854 -0.0201 0.5126 0.9598
5.750 0.8429 0.01550 0.00858 -0.0207 0.5057 0.9610
6.000 0.8703 0.01559 0.00872 -0.0211 0.4953 0.9624
6.250 0.8954 0.01569 0.00880 -0.0211 0.4816 0.9639
6.500 0.9179 0.01585 0.00892 -0.0206 0.4646 0.9657
6.750 0.9387 0.01609 0.00914 -0.0198 0.4499 0.9677
7.000 0.9579 0.01636 0.00944 -0.0187 0.4386 0.9704
7.250 0.9766 0.01667 0.00975 -0.0176 0.4259 0.9727
7.500 0.9983 0.01711 0.01018 -0.0174 0.4044 0.9744
7.750 1.0162 0.01768 0.01074 -0.0168 0.3741 0.9767
8.000 1.0130 0.01908 0.01177 -0.0135 0.2834 0.9820
8.250 0.9942 0.02147 0.01383 -0.0099 0.2306 0.9890
8.500 0.9868 0.02353 0.01575 -0.0076 0.1946 0.9942
8.750 0.9811 0.02609 0.01808 -0.0067 0.1462 0.9988
9.000 0.9662 0.02811 0.01994 -0.0029 0.1149 1.0000
9.250 0.9424 0.03005 0.02169 0.0027 0.0855 1.0000
9.500 0.9248 0.03179 0.02330 0.0074 0.0654 1.0000
9.750 0.9125 0.03338 0.02481 0.0115 0.0502 1.0000
10.000 0.9032 0.03499 0.02633 0.0151 0.0331 1.0000
10.250 0.8983 0.03650 0.02778 0.0180 0.0264 1.0000
10.500 0.8969 0.03796 0.02925 0.0204 0.0235 1.0000
10.750 0.8984 0.03939 0.03071 0.0223 0.0221 1.0000
11.000 0.8999 0.04094 0.03230 0.0241 0.0210 1.0000
11.250 0.9021 0.04256 0.03397 0.0257 0.0201 1.0000
11.500 0.9044 0.04427 0.03575 0.0272 0.0192 1.0000
11.750 0.9081 0.04594 0.03750 0.0284 0.0181 1.0000
12.000 0.9123 0.04764 0.03928 0.0295 0.0182 1.0000
12.250 0.9149 0.04954 0.04125 0.0305 0.0174 1.0000
12.500 0.9169 0.05157 0.04335 0.0315 0.0165 1.0000
12.750 0.9190 0.05365 0.04551 0.0323 0.0162 1.0000
13.000 0.9209 0.05581 0.04772 0.0330 0.0159 1.0000
13.250 0.9220 0.05808 0.05005 0.0337 0.0156 1.0000
13.500 0.9217 0.06051 0.05253 0.0344 0.0152 1.0000
13.750 0.9249 0.06262 0.05468 0.0351 0.0150 1.0000
14.000 0.9301 0.06454 0.05668 0.0357 0.0146 1.0000
14.250 0.9365 0.06635 0.05855 0.0361 0.0144 1.0000
14.500 0.9427 0.06819 0.06048 0.0367 0.0140 1.0000
14.750 0.9495 0.06997 0.06231 0.0372 0.0137 1.0000
15.000 0.9565 0.07174 0.06415 0.0377 0.0133 1.0000
15.250 0.9637 0.07352 0.06599 0.0380 0.0130 1.0000
15.500 0.9706 0.07533 0.06785 0.0384 0.0126 1.0000
15.750 0.9781 0.07708 0.06967 0.0388 0.0124 1.0000
16.000 0.9857 0.07878 0.07141 0.0394 0.0120 1.0000
16.250 0.9940 0.08045 0.07313 0.0398 0.0118 1.0000
16.500 1.0030 0.08201 0.07475 0.0404 0.0116 1.0000
16.750 1.0153 0.08311 0.07587 0.0415 0.0114 1.0000
17.000 1.0221 0.08513 0.07799 0.0418 0.0113 1.0000
17.250 1.0218 0.08826 0.08132 0.0415 0.0111 1.0000
17.500 1.0237 0.09108 0.08429 0.0412 0.0111 1.0000
17.750 1.0207 0.09470 0.08812 0.0405 0.0110 1.0000
18.000 1.0206 0.09787 0.09144 0.0400 0.0110 1.0000
18.250 1.0149 0.10201 0.09578 0.0389 0.0109 1.0000
18.500 1.0101 0.10605 0.09998 0.0377 0.0109 1.0000
18.750 1.0002 0.11108 0.10524 0.0360 0.0108 1.0000
19.000 0.9922 0.11586 0.11021 0.0342 0.0108 1.0000
19.250 0.9822 0.12113 0.11567 0.0320 0.0108 1.0000
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