NACA 2-H-15 AIRFOIL (n2h15-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2-H-15 AIRFOIL (n2h15-il) Reynolds number: 500,000 Max Cl/Cd: 107.47 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n2h15-il-500000-n5.txt Download as CSV file: xf-n2h15-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2-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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1152 0.08301 0.07914 -0.0927 0.6858 0.0267
-10.000 -0.1193 0.07947 0.07563 -0.0942 0.6848 0.0268
-9.750 -0.1230 0.07612 0.07230 -0.0954 0.6838 0.0268
-9.500 -0.1298 0.07254 0.06876 -0.0968 0.6828 0.0268
-9.250 -0.1442 0.06842 0.06465 -0.0992 0.6816 0.0268
-9.000 -0.1577 0.06517 0.06140 -0.0995 0.6804 0.0268
-8.750 -0.1721 0.06224 0.05845 -0.0981 0.6793 0.0268
-8.500 -0.1831 0.05996 0.05614 -0.0956 0.6782 0.0267
-8.000 -0.1882 0.05762 0.05381 -0.0900 0.6763 0.0254
-7.750 -0.2075 0.05539 0.05153 -0.0851 0.6753 0.0251
-7.500 -0.2254 0.05352 0.04959 -0.0798 0.6743 0.0253
-7.250 -0.2443 0.05044 0.04642 -0.0745 0.6733 0.0240
-7.000 -0.2533 0.04792 0.04381 -0.0701 0.6723 0.0240
-6.750 -0.2666 0.04447 0.04021 -0.0646 0.6711 0.0236
-6.500 -0.2729 0.04154 0.03711 -0.0597 0.6698 0.0235
-6.250 -0.2765 0.03875 0.03413 -0.0548 0.6685 0.0235
-6.000 -0.2702 0.03716 0.03244 -0.0516 0.6672 0.0238
-5.750 -0.2626 0.03561 0.03076 -0.0484 0.6660 0.0241
-5.500 -0.2637 0.03254 0.02741 -0.0431 0.6649 0.0238
-5.250 -0.2593 0.03010 0.02472 -0.0387 0.6638 0.0239
-5.000 -0.2516 0.02794 0.02231 -0.0348 0.6629 0.0239
-4.750 -0.2404 0.02608 0.02019 -0.0315 0.6620 0.0240
-4.500 -0.2255 0.02456 0.01845 -0.0289 0.6611 0.0242
-4.250 -0.2087 0.02298 0.01663 -0.0266 0.6602 0.0243
-4.000 -0.1887 0.02154 0.01494 -0.0250 0.6594 0.0245
-3.750 -0.1657 0.02034 0.01352 -0.0240 0.6584 0.0247
-3.500 -0.1402 0.01924 0.01226 -0.0236 0.6572 0.0249
-3.250 -0.1122 0.01830 0.01117 -0.0237 0.6560 0.0254
-3.000 -0.0814 0.01740 0.01013 -0.0244 0.6549 0.0256
-2.750 -0.0473 0.01654 0.00915 -0.0259 0.6538 0.0258
-2.500 -0.0118 0.01580 0.00830 -0.0277 0.6527 0.0262
-2.250 0.0243 0.01518 0.00761 -0.0297 0.6516 0.0265
-2.000 0.0626 0.01462 0.00699 -0.0321 0.6506 0.0267
-1.750 0.1017 0.01406 0.00639 -0.0348 0.6496 0.0270
-1.500 0.1416 0.01340 0.00573 -0.0377 0.6486 0.0274
-1.250 0.1743 0.01302 0.00536 -0.0390 0.6475 0.0278
-1.000 0.2053 0.01273 0.00508 -0.0398 0.6465 0.0283
-0.750 0.2346 0.01251 0.00486 -0.0403 0.6456 0.0288
-0.500 0.2639 0.01228 0.00463 -0.0408 0.6447 0.0294
-0.250 0.2922 0.01212 0.00447 -0.0410 0.6438 0.0300
0.000 0.3206 0.01196 0.00430 -0.0413 0.6429 0.0307
0.250 0.3482 0.01186 0.00424 -0.0415 0.6418 0.0313
0.500 0.3758 0.01179 0.00421 -0.0417 0.6404 0.0316
0.750 0.4039 0.01168 0.00414 -0.0419 0.6390 0.0327
1.000 0.4320 0.01160 0.00409 -0.0422 0.6374 0.0335
1.250 0.4600 0.01155 0.00407 -0.0425 0.6361 0.0346
1.500 0.4880 0.01152 0.00406 -0.0427 0.6348 0.0357
1.750 0.5161 0.01149 0.00405 -0.0430 0.6337 0.0379
2.000 0.5444 0.01145 0.00404 -0.0433 0.6325 0.0411
2.250 0.5733 0.01139 0.00403 -0.0437 0.6314 0.0508
2.750 0.7602 0.01095 0.00610 -0.0737 0.6302 0.9652
3.250 0.8426 0.01147 0.00662 -0.0799 0.6284 0.9814
3.500 0.8759 0.01152 0.00669 -0.0814 0.6272 0.9836
3.750 0.9046 0.01171 0.00693 -0.0820 0.6244 0.9861
4.000 0.9362 0.01170 0.00697 -0.0831 0.6207 0.9878
4.250 0.9700 0.01159 0.00689 -0.0847 0.6183 0.9892
4.500 1.0036 0.01138 0.00667 -0.0861 0.6146 0.9910
4.750 1.0355 0.01132 0.00660 -0.0872 0.6125 0.9929
5.250 1.1043 0.01099 0.00636 -0.0907 0.5964 0.9972
5.500 1.1423 0.01075 0.00614 -0.0934 0.5787 0.9998
5.750 1.1682 0.01087 0.00624 -0.0934 0.5618 1.0000
6.000 1.1906 0.01123 0.00649 -0.0929 0.5314 1.0000
6.250 1.2029 0.01285 0.00775 -0.0919 0.4614 1.0000
6.500 1.1771 0.01771 0.01216 -0.0884 0.3733 1.0000
6.750 1.1421 0.02000 0.01436 -0.0794 0.3520 1.0000
7.000 1.1048 0.02300 0.01715 -0.0713 0.3094 1.0000
7.250 1.0793 0.02582 0.01970 -0.0653 0.2621 1.0000
7.500 1.0481 0.02928 0.02273 -0.0593 0.1836 1.0000
7.750 1.0429 0.03134 0.02456 -0.0562 0.1411 1.0000
8.000 1.0452 0.03299 0.02607 -0.0540 0.1132 1.0000
8.250 1.0480 0.03466 0.02758 -0.0519 0.0834 1.0000
8.500 1.0533 0.03619 0.02896 -0.0501 0.0605 1.0000
8.750 1.0618 0.03753 0.03023 -0.0487 0.0491 1.0000
9.000 1.0727 0.03870 0.03139 -0.0475 0.0430 1.0000
9.250 1.0848 0.03981 0.03249 -0.0464 0.0394 1.0000
9.500 1.0973 0.04089 0.03357 -0.0453 0.0366 1.0000
9.750 1.1089 0.04207 0.03475 -0.0443 0.0342 1.0000
10.000 1.1210 0.04323 0.03593 -0.0432 0.0324 1.0000
10.250 1.1337 0.04433 0.03707 -0.0423 0.0308 1.0000
10.500 1.1457 0.04550 0.03825 -0.0413 0.0295 1.0000
10.750 1.1568 0.04677 0.03953 -0.0404 0.0283 1.0000
11.000 1.1684 0.04803 0.04082 -0.0394 0.0271 1.0000
11.250 1.1804 0.04925 0.04209 -0.0386 0.0263 1.0000
11.500 1.1921 0.05050 0.04338 -0.0377 0.0252 1.0000
11.750 1.2035 0.05177 0.04467 -0.0369 0.0242 1.0000
12.000 1.2131 0.05326 0.04617 -0.0359 0.0230 1.0000
12.250 1.2232 0.05470 0.04764 -0.0351 0.0225 1.0000
12.500 1.2350 0.05599 0.04899 -0.0344 0.0218 1.0000
12.750 1.2462 0.05734 0.05039 -0.0336 0.0210 1.0000
13.000 1.2567 0.05879 0.05188 -0.0329 0.0202 1.0000
13.250 1.2669 0.06026 0.05338 -0.0322 0.0195 1.0000
13.500 1.2753 0.06191 0.05506 -0.0314 0.0189 1.0000
13.750 1.2841 0.06355 0.05673 -0.0307 0.0184 1.0000
14.000 1.2929 0.06521 0.05846 -0.0300 0.0181 1.0000
14.250 1.3023 0.06684 0.06015 -0.0293 0.0175 1.0000
14.500 1.3118 0.06845 0.06182 -0.0288 0.0169 1.0000
14.750 1.3217 0.07001 0.06343 -0.0282 0.0164 1.0000
15.000 1.3298 0.07179 0.06526 -0.0277 0.0159 1.0000
15.250 1.3373 0.07365 0.06716 -0.0272 0.0155 1.0000
15.500 1.3441 0.07560 0.06915 -0.0266 0.0151 1.0000
15.750 1.3493 0.07776 0.07136 -0.0261 0.0148 1.0000
16.000 1.3554 0.07983 0.07351 -0.0256 0.0146 1.0000
16.250 1.3630 0.08174 0.07551 -0.0252 0.0143 1.0000
16.500 1.3694 0.08377 0.07762 -0.0248 0.0140 1.0000
16.750 1.3750 0.08597 0.07990 -0.0245 0.0137 1.0000
17.000 1.3814 0.08807 0.08207 -0.0242 0.0133 1.0000
17.250 1.3855 0.09046 0.08454 -0.0239 0.0132 1.0000
17.500 1.3903 0.09281 0.08696 -0.0238 0.0129 1.0000
17.750 1.3945 0.09523 0.08946 -0.0237 0.0127 1.0000
18.000 1.3986 0.09773 0.09202 -0.0237 0.0123 1.0000
18.250 1.4020 0.10031 0.09466 -0.0238 0.0121 1.0000
18.500 1.4025 0.10328 0.09770 -0.0238 0.0119 1.0000
18.750 1.4021 0.10641 0.10090 -0.0239 0.0117 1.0000
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