NACA 6-H-20 AIRFOIL (n6h20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 6-H-20 AIRFOIL (n6h20-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.95 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n6h20-il-1000000-n5.txt Download as CSV file: xf-n6h20-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 6-H-20 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6936 0.04305 0.03920 -0.0835 0.5973 0.0195
-14.000 -0.7433 0.03780 0.03359 -0.0775 0.5968 0.0197
-13.750 -0.7647 0.03485 0.03039 -0.0727 0.5961 0.0198
-13.500 -0.7735 0.03278 0.02811 -0.0686 0.5953 0.0199
-13.250 -0.7768 0.03105 0.02619 -0.0649 0.5944 0.0201
-13.000 -0.7725 0.02983 0.02482 -0.0619 0.5935 0.0202
-12.750 -0.7673 0.02862 0.02346 -0.0590 0.5926 0.0203
-12.500 -0.7582 0.02766 0.02235 -0.0564 0.5917 0.0205
-12.250 -0.7484 0.02669 0.02125 -0.0539 0.5907 0.0205
-12.000 -0.7371 0.02574 0.02016 -0.0516 0.5897 0.0206
-11.750 -0.7229 0.02506 0.01936 -0.0496 0.5885 0.0207
-11.500 -0.7111 0.02380 0.01795 -0.0474 0.5877 0.0209
-11.250 -0.6954 0.02281 0.01685 -0.0456 0.5872 0.0210
-11.000 -0.6771 0.02216 0.01613 -0.0443 0.5866 0.0212
-10.750 -0.6575 0.02154 0.01544 -0.0431 0.5859 0.0213
-10.500 -0.6373 0.02108 0.01494 -0.0419 0.5851 0.0214
-10.250 -0.6159 0.02057 0.01438 -0.0409 0.5843 0.0215
-10.000 -0.5941 0.02014 0.01390 -0.0400 0.5834 0.0217
-9.750 -0.5707 0.01961 0.01331 -0.0394 0.5827 0.0218
-9.500 -0.5475 0.01922 0.01287 -0.0387 0.5818 0.0220
-9.250 -0.5223 0.01871 0.01229 -0.0385 0.5811 0.0221
-9.000 -0.4980 0.01838 0.01191 -0.0380 0.5802 0.0223
-8.750 -0.4721 0.01796 0.01143 -0.0378 0.5794 0.0225
-8.500 -0.4455 0.01756 0.01098 -0.0377 0.5786 0.0227
-8.250 -0.4172 0.01710 0.01046 -0.0380 0.5778 0.0229
-8.000 -0.3889 0.01671 0.01000 -0.0382 0.5770 0.0231
-7.750 -0.3592 0.01627 0.00951 -0.0387 0.5762 0.0233
-7.500 -0.3303 0.01593 0.00911 -0.0391 0.5754 0.0235
-7.250 -0.3008 0.01559 0.00872 -0.0396 0.5745 0.0237
-7.000 -0.2710 0.01527 0.00835 -0.0401 0.5736 0.0239
-6.750 -0.2410 0.01496 0.00800 -0.0406 0.5726 0.0240
-6.500 -0.2116 0.01470 0.00770 -0.0411 0.5716 0.0241
-6.250 -0.1821 0.01445 0.00743 -0.0415 0.5711 0.0243
-6.000 -0.1523 0.01420 0.00716 -0.0420 0.5706 0.0244
-5.750 -0.1207 0.01385 0.00680 -0.0429 0.5700 0.0247
-5.500 -0.0901 0.01356 0.00652 -0.0436 0.5694 0.0250
-5.250 -0.0604 0.01335 0.00630 -0.0441 0.5688 0.0253
-5.000 -0.0314 0.01317 0.00613 -0.0444 0.5682 0.0255
-4.750 -0.0027 0.01301 0.00598 -0.0448 0.5675 0.0259
-4.500 0.0258 0.01286 0.00583 -0.0451 0.5669 0.0263
-4.250 0.0545 0.01271 0.00569 -0.0454 0.5662 0.0267
-4.000 0.0830 0.01257 0.00556 -0.0457 0.5655 0.0270
-3.750 0.1114 0.01244 0.00542 -0.0460 0.5648 0.0273
-3.500 0.1395 0.01233 0.00531 -0.0462 0.5640 0.0278
-3.250 0.1675 0.01221 0.00519 -0.0464 0.5632 0.0280
-3.000 0.1953 0.01210 0.00508 -0.0466 0.5623 0.0283
-2.750 0.2227 0.01201 0.00499 -0.0467 0.5615 0.0285
-2.500 0.2501 0.01190 0.00488 -0.0468 0.5605 0.0289
-2.250 0.2772 0.01179 0.00478 -0.0469 0.5592 0.0296
-2.000 0.3039 0.01172 0.00471 -0.0469 0.5580 0.0301
-1.750 0.3303 0.01166 0.00465 -0.0468 0.5567 0.0309
-1.500 0.3566 0.01160 0.00461 -0.0468 0.5558 0.0317
-1.250 0.3828 0.01153 0.00456 -0.0467 0.5553 0.0325
-1.000 0.4089 0.01147 0.00452 -0.0466 0.5548 0.0334
-0.750 0.4346 0.01140 0.00449 -0.0464 0.5541 0.0350
-0.500 0.4600 0.01134 0.00446 -0.0463 0.5534 0.0370
-0.250 0.4853 0.01128 0.00443 -0.0461 0.5525 0.0392
0.000 0.5099 0.01121 0.00441 -0.0457 0.5515 0.0476
0.250 0.5337 0.01111 0.00440 -0.0453 0.5505 0.0668
0.500 0.5562 0.01100 0.00438 -0.0446 0.5494 0.0942
0.750 0.5711 0.01072 0.00439 -0.0424 0.5482 0.1916
1.000 0.5900 0.01057 0.00435 -0.0410 0.5472 0.2308
1.250 0.5917 0.01010 0.00420 -0.0364 0.5463 0.3424
1.500 0.5863 0.00955 0.00392 -0.0304 0.5451 0.4426
1.750 0.5627 0.00907 0.00364 -0.0204 0.5440 0.5221
2.000 0.5293 0.00874 0.00352 -0.0078 0.5427 0.6034
2.250 0.4938 0.00800 0.00322 0.0053 0.5415 0.7563
2.500 0.5117 0.00821 0.00360 0.0073 0.5404 0.8254
2.750 0.5382 0.00836 0.00377 0.0073 0.5395 0.8325
3.000 0.5630 0.00846 0.00385 0.0076 0.5385 0.8367
3.250 0.5930 0.00872 0.00417 0.0068 0.5372 0.8413
3.500 0.6206 0.00899 0.00445 0.0065 0.5355 0.8465
3.750 0.6457 0.00910 0.00455 0.0067 0.5333 0.8485
4.000 0.6710 0.00917 0.00460 0.0067 0.5312 0.8491
4.250 0.6980 0.00927 0.00470 0.0064 0.5290 0.8505
4.500 0.7237 0.00939 0.00481 0.0062 0.5263 0.8513
4.750 0.7500 0.00954 0.00499 0.0060 0.5237 0.8523
5.000 0.7763 0.00972 0.00521 0.0057 0.5211 0.8535
5.250 0.8002 0.00989 0.00539 0.0059 0.5179 0.8547
5.500 0.8203 0.01001 0.00551 0.0067 0.5145 0.8550
5.750 0.8351 0.01020 0.00568 0.0083 0.5108 0.8552
6.000 0.8442 0.01045 0.00596 0.0109 0.5079 0.8555
6.250 0.8394 0.01099 0.00652 0.0158 0.5037 0.8561
6.500 0.8400 0.01164 0.00716 0.0195 0.4993 0.8565
6.750 0.8414 0.01234 0.00785 0.0229 0.4951 0.8569
7.000 0.8462 0.01300 0.00853 0.0257 0.4899 0.8572
7.250 0.8474 0.01380 0.00932 0.0290 0.4849 0.8576
7.500 0.8471 0.01468 0.01019 0.0324 0.4802 0.8579
7.750 0.8486 0.01555 0.01106 0.0354 0.4740 0.8583
8.000 0.8396 0.01682 0.01229 0.0398 0.4662 0.8587
8.250 0.8407 0.01777 0.01324 0.0427 0.4583 0.8591
8.500 0.8285 0.01934 0.01476 0.0471 0.4465 0.8596
8.750 0.8167 0.02102 0.01638 0.0513 0.4342 0.8599
9.000 0.8075 0.02268 0.01799 0.0549 0.4217 0.8602
9.250 0.8019 0.02424 0.01950 0.0580 0.4078 0.8604
9.500 0.7982 0.02580 0.02101 0.0607 0.3964 0.8606
9.750 0.7914 0.02756 0.02270 0.0637 0.3808 0.8609
10.000 0.7786 0.02974 0.02479 0.0670 0.3621 0.8611
10.250 0.7828 0.03105 0.02606 0.0686 0.3527 0.8612
10.500 0.7773 0.03298 0.02792 0.0710 0.3377 0.8614
10.750 0.7781 0.03456 0.02943 0.0726 0.3230 0.8615
11.000 0.7845 0.03588 0.03072 0.0737 0.3134 0.8616
11.250 0.7844 0.03762 0.03238 0.0753 0.2974 0.8617
11.500 0.7803 0.03965 0.03429 0.0771 0.2748 0.8618
11.750 0.7836 0.04127 0.03585 0.0782 0.2607 0.8619
12.000 0.7821 0.04323 0.03769 0.0796 0.2401 0.8620
12.250 0.7939 0.04436 0.03880 0.0799 0.2332 0.8622
12.500 0.7995 0.04597 0.04035 0.0805 0.2234 0.8624
12.750 0.8138 0.04696 0.04136 0.0804 0.2203 0.8626
13.000 0.8294 0.04789 0.04230 0.0803 0.2178 0.8628
13.250 0.8419 0.04904 0.04343 0.0803 0.2131 0.8630
13.500 0.8551 0.05016 0.04456 0.0802 0.2089 0.8632
13.750 0.8698 0.05118 0.04561 0.0800 0.2066 0.8634
14.000 0.8826 0.05236 0.04680 0.0799 0.2021 0.8636
14.250 0.8968 0.05342 0.04788 0.0797 0.1990 0.8637
14.500 0.9108 0.05451 0.04898 0.0795 0.1960 0.8639
14.750 0.9224 0.05579 0.05026 0.0794 0.1906 0.8641
15.000 0.9376 0.05680 0.05130 0.0790 0.1859 0.8643
15.250 0.9272 0.05994 0.05421 0.0800 0.1463 0.8645
15.500 0.9227 0.06256 0.05667 0.0807 0.1218 0.8647
15.750 0.9280 0.06448 0.05857 0.0808 0.1143 0.8649
16.000 0.9352 0.06624 0.06033 0.0807 0.1081 0.8651
16.250 0.9458 0.06773 0.06183 0.0804 0.1053 0.8653
16.500 0.9558 0.06926 0.06338 0.0801 0.1016 0.8654
16.750 0.9670 0.07073 0.06489 0.0797 0.0994 0.8656
17.000 0.9781 0.07221 0.06640 0.0793 0.0971 0.8658
17.250 0.9873 0.07384 0.06805 0.0790 0.0924 0.8660
17.500 0.9971 0.07543 0.06966 0.0786 0.0900 0.8662
17.750 1.0067 0.07707 0.07133 0.0781 0.0869 0.8664
18.000 1.0123 0.07911 0.07336 0.0778 0.0789 0.8666
18.250 1.0196 0.08099 0.07523 0.0774 0.0732 0.8668
18.500 1.0196 0.08359 0.07776 0.0772 0.0626 0.8670
18.750 1.0229 0.08591 0.08008 0.0768 0.0577 0.8672
19.000 1.0306 0.08778 0.08198 0.0763 0.0556 0.8674
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Polar data table (+)
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