NACA 5-H-20 AIRFOIL (n5h20-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 5-H-20 AIRFOIL (n5h20-il) Reynolds number: 500,000 Max Cl/Cd: 78.58 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n5h20-il-500000.txt Download as CSV file: xf-n5h20-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 5-H-20 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3010 0.07338 0.06980 -0.0709 0.6559 0.0422
-11.250 -0.3441 0.06683 0.06312 -0.0725 0.6551 0.0422
-11.000 -0.3788 0.06226 0.05842 -0.0713 0.6538 0.0423
-10.750 -0.3635 0.05734 0.05358 -0.0723 0.6518 0.0427
-10.500 -0.3717 0.05424 0.05042 -0.0712 0.6500 0.0428
-10.250 -0.3859 0.05118 0.04726 -0.0691 0.6483 0.0429
-10.000 -0.3919 0.04885 0.04486 -0.0671 0.6463 0.0431
-9.750 -0.4021 0.04646 0.04240 -0.0643 0.6445 0.0433
-9.500 -0.4129 0.04413 0.04001 -0.0609 0.6429 0.0434
-9.250 -0.4195 0.04218 0.03801 -0.0575 0.6412 0.0437
-9.000 -0.4290 0.04021 0.03596 -0.0533 0.6393 0.0440
-8.750 -0.4306 0.03832 0.03399 -0.0501 0.6375 0.0445
-8.500 -0.4322 0.03612 0.03166 -0.0468 0.6356 0.0452
-8.250 -0.4740 0.03457 0.02936 -0.0351 0.6339 0.0482
-8.000 -0.4692 0.02924 0.02395 -0.0337 0.6324 0.0489
-7.750 -0.4525 0.02732 0.02199 -0.0329 0.6305 0.0493
-7.500 -0.4372 0.02576 0.02035 -0.0317 0.6285 0.0498
-7.250 -0.4219 0.02431 0.01884 -0.0303 0.6269 0.0503
-7.000 -0.4459 0.02894 0.02197 -0.0221 0.6274 0.0429
-6.750 -0.4166 0.02707 0.02011 -0.0227 0.6260 0.0408
-6.500 -0.3929 0.02523 0.01807 -0.0221 0.6245 0.0403
-6.250 -0.3663 0.02369 0.01634 -0.0219 0.6229 0.0402
-6.000 -0.3352 0.02214 0.01461 -0.0226 0.6212 0.0398
-5.750 -0.3024 0.02097 0.01328 -0.0237 0.6196 0.0399
-5.500 -0.2670 0.01994 0.01214 -0.0252 0.6180 0.0401
-5.250 -0.2300 0.01906 0.01118 -0.0271 0.6164 0.0404
-5.000 -0.1899 0.01825 0.01029 -0.0297 0.6150 0.0409
-4.750 -0.1496 0.01760 0.00956 -0.0323 0.6135 0.0415
-4.500 -0.1190 0.01732 0.00919 -0.0329 0.6120 0.0422
-4.250 -0.0721 0.01655 0.00844 -0.0369 0.6102 0.0431
-4.000 -0.0402 0.01615 0.00810 -0.0379 0.6092 0.0438
-3.750 -0.0111 0.01584 0.00783 -0.0383 0.6079 0.0447
-3.500 0.0170 0.01555 0.00755 -0.0386 0.6060 0.0456
-3.250 0.0441 0.01529 0.00730 -0.0386 0.6043 0.0466
-3.000 0.0704 0.01506 0.00707 -0.0385 0.6024 0.0476
-2.750 0.0960 0.01476 0.00677 -0.0382 0.6007 0.0488
-2.500 0.1208 0.01450 0.00653 -0.0379 0.5991 0.0506
-2.250 0.1460 0.01434 0.00638 -0.0376 0.5977 0.0529
-2.000 0.1712 0.01422 0.00624 -0.0373 0.5965 0.0549
-1.750 0.1952 0.01401 0.00605 -0.0368 0.5953 0.0583
-1.500 0.2199 0.01395 0.00598 -0.0364 0.5940 0.0620
-1.250 0.2436 0.01386 0.00593 -0.0359 0.5926 0.0692
-1.000 0.2664 0.01365 0.00582 -0.0351 0.5917 0.0870
-0.750 0.2636 0.01256 0.00573 -0.0300 0.5907 0.3458
-0.500 0.2358 0.01170 0.00552 -0.0197 0.5896 0.5191
-0.250 0.2024 0.01123 0.00540 -0.0075 0.5884 0.6060
0.000 0.1988 0.01195 0.00688 0.0002 0.5872 0.8308
0.250 0.2548 0.01375 0.00868 -0.0041 0.5859 0.8523
0.500 0.5049 0.01884 0.01361 -0.0432 0.5822 0.8912
0.750 0.6684 0.01859 0.01323 -0.0678 0.5802 0.9316
1.000 0.6617 0.02038 0.01501 -0.0613 0.5790 0.9385
1.250 0.6936 0.01976 0.01436 -0.0626 0.5779 0.9390
1.500 0.7243 0.01938 0.01395 -0.0636 0.5765 0.9394
1.750 0.7551 0.01906 0.01361 -0.0648 0.5749 0.9400
2.000 0.7861 0.01870 0.01329 -0.0659 0.5733 0.9407
2.250 0.8151 0.01849 0.01310 -0.0667 0.5719 0.9413
2.500 0.8426 0.01835 0.01298 -0.0671 0.5703 0.9418
2.750 0.8693 0.01823 0.01288 -0.0674 0.5687 0.9424
3.000 0.8958 0.01813 0.01278 -0.0676 0.5671 0.9429
3.250 0.9221 0.01805 0.01272 -0.0679 0.5658 0.9435
3.500 0.9485 0.01796 0.01263 -0.0681 0.5644 0.9442
3.750 0.9749 0.01783 0.01248 -0.0682 0.5624 0.9450
4.000 1.0010 0.01775 0.01237 -0.0683 0.5604 0.9458
4.250 1.0261 0.01775 0.01238 -0.0683 0.5580 0.9469
4.500 1.0501 0.01781 0.01250 -0.0681 0.5561 0.9492
4.750 1.0487 0.01897 0.01373 -0.0627 0.5535 0.9538
5.000 1.0771 0.01858 0.01337 -0.0634 0.5512 0.9542
5.250 1.1055 0.01824 0.01306 -0.0640 0.5488 0.9545
5.500 1.1337 0.01796 0.01279 -0.0647 0.5467 0.9549
5.750 1.1617 0.01772 0.01255 -0.0652 0.5444 0.9553
6.000 1.1894 0.01759 0.01241 -0.0657 0.5423 0.9558
6.250 1.2158 0.01748 0.01239 -0.0662 0.5396 0.9564
6.500 1.2421 0.01732 0.01232 -0.0666 0.5348 0.9572
6.750 1.2687 0.01716 0.01218 -0.0669 0.5304 0.9580
7.000 1.2951 0.01701 0.01200 -0.0671 0.5260 0.9589
7.250 1.3188 0.01705 0.01217 -0.0672 0.5203 0.9602
7.500 1.3422 0.01708 0.01224 -0.0670 0.5143 0.9619
7.750 1.1667 0.01760 0.01274 -0.0285 0.5208 0.9203
8.000 1.2732 0.01764 0.01280 -0.0444 0.5099 0.9308
8.250 1.3077 0.01796 0.01326 -0.0466 0.5023 0.9418
8.500 1.3398 0.01807 0.01339 -0.0484 0.4933 0.9448
8.750 0.9516 0.01650 0.01169 0.0295 0.5124 0.9222
9.000 0.9541 0.01681 0.01202 0.0327 0.5074 0.9226
9.250 0.9418 0.01746 0.01275 0.0378 0.5009 0.9239
9.500 0.9542 0.01759 0.01283 0.0395 0.4939 0.9244
9.750 0.9399 0.01876 0.01409 0.0444 0.4854 0.9254
10.000 0.9378 0.01959 0.01493 0.0476 0.4747 0.9261
10.250 0.9311 0.02073 0.01607 0.0512 0.4603 0.9268
10.500 0.9207 0.02223 0.01752 0.0550 0.4366 0.9277
10.750 0.8842 0.02506 0.02007 0.0614 0.3884 0.9289
11.000 0.8553 0.02786 0.02267 0.0665 0.3620 0.9299
11.250 0.8456 0.02981 0.02452 0.0695 0.3474 0.9306
11.500 0.8450 0.03128 0.02591 0.0715 0.3372 0.9312
11.750 0.8546 0.03226 0.02690 0.0725 0.3313 0.9317
12.000 0.8610 0.03342 0.02802 0.0737 0.3239 0.9322
12.250 0.8718 0.03435 0.02895 0.0745 0.3183 0.9328
12.500 0.8816 0.03540 0.03003 0.0753 0.3113 0.9335
12.750 0.8891 0.03657 0.03116 0.0763 0.3044 0.9343
13.000 0.9010 0.03755 0.03219 0.0768 0.2987 0.9349
13.250 0.9113 0.03866 0.03331 0.0773 0.2913 0.9354
13.500 0.9200 0.03986 0.03450 0.0780 0.2847 0.9360
13.750 0.9316 0.04100 0.03570 0.0783 0.2769 0.9365
14.000 0.9387 0.04239 0.03708 0.0789 0.2677 0.9371
14.250 0.9459 0.04387 0.03856 0.0794 0.2544 0.9376
14.500 0.9501 0.04556 0.04021 0.0801 0.2404 0.9382
14.750 0.9471 0.04800 0.04252 0.0808 0.2194 0.9390
15.000 0.9500 0.05004 0.04450 0.0810 0.2037 0.9397
15.250 0.9506 0.05228 0.04663 0.0813 0.1781 0.9405
15.500 0.9470 0.05496 0.04915 0.0817 0.1496 0.9413
15.750 0.9470 0.05740 0.05148 0.0818 0.1344 0.9421
16.000 0.9541 0.05927 0.05334 0.0815 0.1277 0.9429
16.250 0.9588 0.06141 0.05547 0.0812 0.1215 0.9437
16.500 0.9680 0.06319 0.05729 0.0807 0.1154 0.9446
16.750 0.9748 0.06525 0.05935 0.0802 0.1102 0.9454
17.000 0.9852 0.06706 0.06121 0.0794 0.1034 0.9463
17.250 0.9906 0.06934 0.06350 0.0788 0.0951 0.9472
17.500 1.0005 0.07125 0.06539 0.0779 0.0778 0.9482
17.750 0.9987 0.07438 0.06839 0.0773 0.0642 0.9491
18.000 0.9990 0.07742 0.07139 0.0764 0.0584 0.9500
18.250 1.0031 0.08024 0.07426 0.0752 0.0556 0.9510
18.500 1.0045 0.08336 0.07741 0.0741 0.0531 0.9519
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