NACA 5-H-15 AIRFOIL (n5h15-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 5-H-15 AIRFOIL (n5h15-il) Reynolds number: 100,000 Max Cl/Cd: 43.08 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n5h15-il-100000-n5.txt Download as CSV file: xf-n5h15-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4099 0.12456 0.11947 -0.0328 0.8088 0.0692
-12.000 -0.3981 0.12093 0.11581 -0.0332 0.8054 0.0700
-11.750 -0.3923 0.11717 0.11204 -0.0346 0.8023 0.0706
-11.500 -0.4195 0.10664 0.10152 -0.0433 0.8003 0.0556
-11.250 -0.4116 0.10308 0.09793 -0.0434 0.7976 0.0551
-11.000 -0.4089 0.09898 0.09381 -0.0447 0.7947 0.0546
-10.750 -0.4064 0.09491 0.08975 -0.0462 0.7912 0.0536
-10.500 -0.4104 0.08992 0.08476 -0.0489 0.7880 0.0527
-10.250 -0.4231 0.08354 0.07839 -0.0533 0.7851 0.0516
-10.000 -0.4442 0.07732 0.07210 -0.0566 0.7824 0.0506
-9.750 -0.4673 0.07216 0.06684 -0.0577 0.7794 0.0498
-9.500 -0.4897 0.06781 0.06237 -0.0569 0.7757 0.0493
-9.250 -0.5114 0.06419 0.05857 -0.0542 0.7721 0.0487
-9.000 -0.5273 0.06122 0.05540 -0.0509 0.7690 0.0486
-8.750 -0.5354 0.05838 0.05232 -0.0480 0.7664 0.0489
-8.500 -0.5376 0.05571 0.04942 -0.0458 0.7628 0.0496
-8.250 -0.5378 0.05302 0.04648 -0.0434 0.7591 0.0502
-8.000 -0.5361 0.05034 0.04348 -0.0407 0.7560 0.0505
-7.750 -0.5320 0.04768 0.04048 -0.0381 0.7534 0.0504
-7.500 -0.5249 0.04523 0.03767 -0.0355 0.7512 0.0504
-7.250 -0.5137 0.04297 0.03508 -0.0336 0.7481 0.0505
-7.000 -0.5001 0.04090 0.03266 -0.0320 0.7445 0.0507
-6.750 -0.4849 0.03911 0.03053 -0.0303 0.7412 0.0513
-6.500 -0.4681 0.03757 0.02864 -0.0287 0.7385 0.0525
-6.250 -0.4497 0.03612 0.02683 -0.0271 0.7363 0.0534
-6.000 -0.4284 0.03467 0.02508 -0.0262 0.7336 0.0538
-5.750 -0.4048 0.03333 0.02347 -0.0259 0.7295 0.0541
-5.500 -0.3806 0.03209 0.02197 -0.0254 0.7258 0.0544
-5.250 -0.3555 0.03093 0.02056 -0.0248 0.7226 0.0549
-5.000 -0.3297 0.02986 0.01923 -0.0242 0.7199 0.0554
-4.750 -0.3011 0.02887 0.01814 -0.0247 0.7137 0.0559
-4.500 -0.2722 0.02756 0.01683 -0.0252 0.7091 0.0577
-4.250 -0.2454 0.02665 0.01588 -0.0249 0.7058 0.0596
-4.000 -0.2179 0.02596 0.01514 -0.0251 0.7014 0.0615
-3.750 -0.1903 0.02532 0.01448 -0.0254 0.6970 0.0628
-3.500 -0.1644 0.02468 0.01380 -0.0251 0.6936 0.0641
-3.250 -0.1400 0.02408 0.01313 -0.0244 0.6909 0.0657
-3.000 -0.1167 0.02358 0.01253 -0.0235 0.6885 0.0674
-2.750 -0.0947 0.02327 0.01226 -0.0230 0.6831 0.0694
-2.500 -0.0728 0.02284 0.01181 -0.0221 0.6792 0.0726
-2.250 -0.0495 0.02245 0.01135 -0.0212 0.6761 0.0780
-2.000 -0.0253 0.02199 0.01084 -0.0204 0.6737 0.0857
-1.750 -0.0014 0.02184 0.01080 -0.0202 0.6680 0.0984
-1.500 0.0791 0.02038 0.01242 -0.0277 0.6652 0.8376
-1.250 0.1270 0.02174 0.01359 -0.0290 0.6620 0.8926
-1.000 0.2328 0.02290 0.01448 -0.0414 0.6598 0.9437
-0.750 0.2804 0.02266 0.01408 -0.0454 0.6566 0.9518
-0.500 0.3064 0.02275 0.01412 -0.0459 0.6508 0.9557
-0.250 0.3302 0.02267 0.01395 -0.0455 0.6469 0.9593
0.000 0.3609 0.02238 0.01353 -0.0463 0.6438 0.9616
0.250 0.3900 0.02234 0.01345 -0.0472 0.6388 0.9644
0.500 0.4168 0.02232 0.01340 -0.0476 0.6334 0.9671
0.750 0.4426 0.02218 0.01319 -0.0475 0.6297 0.9703
1.000 0.4689 0.02197 0.01289 -0.0474 0.6269 0.9729
1.250 0.4975 0.02214 0.01310 -0.0486 0.6199 0.9749
1.500 0.5260 0.02203 0.01297 -0.0491 0.6157 0.9773
1.750 0.5537 0.02185 0.01273 -0.0494 0.6126 0.9798
2.000 0.5790 0.02204 0.01296 -0.0497 0.6069 0.9822
2.250 0.6055 0.02210 0.01304 -0.0500 0.6018 0.9844
2.500 0.6350 0.02194 0.01287 -0.0507 0.5984 0.9864
2.750 0.6632 0.02186 0.01277 -0.0512 0.5950 0.9884
3.000 0.6889 0.02221 0.01323 -0.0518 0.5884 0.9905
3.250 0.7161 0.02222 0.01326 -0.0522 0.5845 0.9927
3.500 0.7442 0.02211 0.01315 -0.0525 0.5817 0.9945
3.750 0.7705 0.02247 0.01363 -0.0533 0.5759 0.9964
4.000 0.7976 0.02264 0.01387 -0.0539 0.5712 0.9984
4.250 0.8254 0.02263 0.01390 -0.0543 0.5681 1.0000
4.500 0.8478 0.02263 0.01393 -0.0534 0.5658 1.0000
4.750 0.8639 0.02348 0.01495 -0.0526 0.5595 1.0000
5.000 0.8833 0.02384 0.01539 -0.0517 0.5559 1.0000
5.250 0.9040 0.02403 0.01567 -0.0508 0.5533 1.0000
5.500 0.9257 0.02414 0.01585 -0.0499 0.5513 1.0000
5.750 0.9372 0.02525 0.01713 -0.0486 0.5459 1.0000
6.000 0.9526 0.02584 0.01784 -0.0472 0.5417 1.0000
6.250 0.9733 0.02587 0.01798 -0.0461 0.5385 1.0000
6.500 0.9911 0.02602 0.01823 -0.0447 0.5336 1.0000
6.750 1.0053 0.02616 0.01847 -0.0427 0.5250 1.0000
7.000 1.0212 0.02591 0.01830 -0.0405 0.5142 1.0000
7.250 1.0402 0.02538 0.01781 -0.0386 0.5025 1.0000
7.500 1.0598 0.02492 0.01740 -0.0367 0.4910 1.0000
7.750 1.0693 0.02509 0.01764 -0.0339 0.4780 1.0000
8.000 1.0797 0.02506 0.01761 -0.0310 0.4617 1.0000
8.250 1.0807 0.02550 0.01805 -0.0270 0.4450 1.0000
8.500 1.0763 0.02610 0.01863 -0.0224 0.4296 1.0000
8.750 1.0503 0.02737 0.01997 -0.0152 0.4214 1.0000
9.000 1.0346 0.02836 0.02097 -0.0095 0.4098 1.0000
9.250 1.0185 0.02956 0.02217 -0.0042 0.3960 1.0000
9.500 1.0000 0.03112 0.02376 0.0010 0.3815 1.0000
9.750 0.9795 0.03313 0.02585 0.0057 0.3642 1.0000
10.000 0.9641 0.03439 0.02658 0.0105 0.2758 1.0000
10.250 0.9416 0.03680 0.02858 0.0149 0.2437 1.0000
10.500 0.9210 0.03957 0.03113 0.0185 0.2127 1.0000
10.750 0.9059 0.04225 0.03366 0.0212 0.1841 1.0000
11.000 0.8906 0.04522 0.03644 0.0235 0.1514 1.0000
11.250 0.8768 0.04830 0.03930 0.0254 0.1184 1.0000
11.500 0.8649 0.05135 0.04211 0.0271 0.0848 1.0000
11.750 0.8578 0.05404 0.04460 0.0285 0.0626 1.0000
12.000 0.8564 0.05627 0.04676 0.0298 0.0498 1.0000
12.250 0.8572 0.05837 0.04882 0.0309 0.0403 1.0000
12.500 0.8599 0.06035 0.05080 0.0319 0.0357 1.0000
12.750 0.8639 0.06224 0.05271 0.0327 0.0322 1.0000
13.000 0.8675 0.06422 0.05470 0.0335 0.0303 1.0000
13.250 0.8723 0.06616 0.05676 0.0342 0.0290 1.0000
13.500 0.8765 0.06818 0.05887 0.0348 0.0279 1.0000
13.750 0.8805 0.07026 0.06103 0.0353 0.0270 1.0000
14.000 0.8835 0.07248 0.06331 0.0359 0.0258 1.0000
14.250 0.8871 0.07465 0.06553 0.0363 0.0252 1.0000
14.500 0.8917 0.07668 0.06762 0.0368 0.0245 1.0000
14.750 0.8981 0.07855 0.06959 0.0373 0.0235 1.0000
15.000 0.9046 0.08040 0.07153 0.0378 0.0226 1.0000
15.250 0.9119 0.08215 0.07338 0.0383 0.0220 1.0000
15.500 0.9205 0.08375 0.07504 0.0389 0.0215 1.0000
15.750 0.9301 0.08522 0.07658 0.0395 0.0211 1.0000
16.000 0.9403 0.08662 0.07802 0.0403 0.0206 1.0000
16.250 0.9514 0.08799 0.07945 0.0410 0.0202 1.0000
16.500 0.9639 0.08926 0.08078 0.0419 0.0199 1.0000
16.750 0.9735 0.09113 0.08278 0.0425 0.0196 1.0000
17.000 0.9766 0.09392 0.08578 0.0423 0.0194 1.0000
17.250 0.9743 0.09758 0.08970 0.0417 0.0190 1.0000
17.500 0.9727 0.10115 0.09348 0.0410 0.0188 1.0000
17.750 0.9651 0.10570 0.09828 0.0397 0.0184 1.0000
18.000 0.9606 0.10990 0.10268 0.0386 0.0185 1.0000
18.250 0.9497 0.11522 0.10824 0.0365 0.0182 1.0000
18.500 0.9394 0.12060 0.11383 0.0344 0.0182 1.0000
18.750 0.9241 0.12710 0.12056 0.0314 0.0181 1.0000
19.000 0.9091 0.13383 0.12749 0.0281 0.0181 1.0000
19.250 0.8918 0.14146 0.13532 0.0241 0.0183 1.0000
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