AH 94-W-301 (ah94w301-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 94-W-301 (ah94w301-il) Reynolds number: 100,000 Max Cl/Cd: 23.43 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah94w301-il-100000-n5.txt Download as CSV file: xf-ah94w301-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 94-W-301
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3158 0.10251 0.09407 -0.0570 0.7766 0.2553
-11.000 -0.3269 0.09439 0.08574 -0.0591 0.7565 0.2688
-10.750 -0.3020 0.09438 0.08564 -0.0593 0.7447 0.2698
-10.500 -0.2783 0.09417 0.08540 -0.0596 0.7335 0.2713
-9.000 -0.2516 0.07873 0.06955 -0.0632 0.6902 0.3016
-8.750 -0.2262 0.07875 0.06956 -0.0633 0.6824 0.3027
-8.500 -0.2023 0.07861 0.06937 -0.0634 0.6754 0.3043
-8.250 -0.1812 0.07816 0.06884 -0.0635 0.6694 0.3065
-8.000 -0.1673 0.07680 0.06748 -0.0638 0.6629 0.3103
-7.250 -0.2019 0.06461 0.05508 -0.0652 0.6502 0.3349
-7.000 -0.1752 0.06477 0.05518 -0.0652 0.6453 0.3358
-6.750 -0.1491 0.06483 0.05528 -0.0654 0.6393 0.3371
-6.500 -0.1247 0.06474 0.05518 -0.0654 0.6336 0.3388
-6.250 -0.1042 0.06427 0.05467 -0.0654 0.6286 0.3413
-5.500 -0.1546 0.05162 0.04183 -0.0655 0.6188 0.3700
-5.250 -0.1262 0.05201 0.04225 -0.0654 0.6135 0.3708
-5.000 -0.0993 0.05223 0.04247 -0.0653 0.6088 0.3719
-4.750 -0.0741 0.05227 0.04248 -0.0652 0.6046 0.3733
-4.500 -0.0507 0.05213 0.04230 -0.0650 0.6009 0.3754
-4.250 -0.0371 0.05114 0.04131 -0.0648 0.5969 0.3796
-3.250 -0.1589 0.03313 0.02286 -0.0620 0.5845 0.4249
-3.000 -0.1278 0.03352 0.02327 -0.0618 0.5809 0.4262
-2.750 -0.0968 0.03391 0.02366 -0.0618 0.5778 0.4277
-2.500 -0.0693 0.03423 0.02406 -0.0616 0.5739 0.4296
-2.250 -0.0444 0.03434 0.02423 -0.0614 0.5695 0.4320
-2.000 -0.0237 0.03383 0.02370 -0.0616 0.5654 0.4361
-1.750 -0.0117 0.03160 0.02121 -0.0639 0.5619 0.4448
-1.500 0.0173 0.03186 0.02150 -0.0637 0.5586 0.4465
-1.250 0.0464 0.03208 0.02172 -0.0637 0.5558 0.4485
-1.000 0.0728 0.03224 0.02193 -0.0637 0.5526 0.4509
-0.750 0.0967 0.03220 0.02195 -0.0638 0.5487 0.4542
-0.500 0.1207 0.03164 0.02135 -0.0648 0.5448 0.4590
-0.250 0.1468 0.03084 0.02041 -0.0666 0.5412 0.4647
0.000 0.1746 0.03104 0.02067 -0.0664 0.5379 0.4666
0.250 0.2033 0.03119 0.02082 -0.0664 0.5351 0.4688
0.500 0.2327 0.03127 0.02086 -0.0668 0.5327 0.4716
0.750 0.2560 0.03137 0.02106 -0.0668 0.5290 0.4749
1.000 0.2813 0.03119 0.02090 -0.0677 0.5253 0.4794
1.250 0.3096 0.03081 0.02043 -0.0693 0.5218 0.4847
1.500 0.3357 0.03104 0.02074 -0.0690 0.5186 0.4867
1.750 0.3635 0.03120 0.02093 -0.0689 0.5157 0.4891
2.000 0.3929 0.03126 0.02098 -0.0693 0.5132 0.4919
2.250 0.4228 0.03128 0.02097 -0.0700 0.5108 0.4953
2.500 0.4443 0.03150 0.02130 -0.0700 0.5070 0.4993
2.750 0.4712 0.03145 0.02121 -0.0715 0.5033 0.5049
3.000 0.4940 0.03180 0.02168 -0.0707 0.5000 0.5070
3.250 0.5192 0.03204 0.02200 -0.0703 0.4970 0.5094
3.500 0.5473 0.03216 0.02214 -0.0705 0.4943 0.5122
3.750 0.5781 0.03218 0.02213 -0.0712 0.4921 0.5155
4.000 0.6097 0.03220 0.02210 -0.0723 0.4900 0.5196
4.250 0.6251 0.03281 0.02284 -0.0717 0.4858 0.5242
4.500 0.6428 0.03334 0.02348 -0.0709 0.4819 0.5275
4.750 0.6623 0.03380 0.02405 -0.0698 0.4785 0.5299
5.000 0.6863 0.03406 0.02438 -0.0693 0.4757 0.5327
5.250 0.7151 0.03417 0.02450 -0.0697 0.4733 0.5359
5.500 0.7472 0.03421 0.02452 -0.0706 0.4714 0.5398
5.750 0.7781 0.03436 0.02463 -0.0717 0.4693 0.5445
6.000 0.7684 0.03598 0.02646 -0.0679 0.4636 0.5483
6.250 0.7712 0.03702 0.02768 -0.0648 0.4593 0.5504
6.500 0.7867 0.03759 0.02834 -0.0633 0.4562 0.5531
6.750 0.8104 0.03789 0.02869 -0.0629 0.4539 0.5563
7.000 0.8430 0.03790 0.02870 -0.0638 0.4520 0.5600
7.250 0.8831 0.03769 0.02844 -0.0657 0.4504 0.5646
7.500 0.7333 0.04711 0.03834 -0.0507 0.4354 0.5636
7.750 0.7659 0.04700 0.03820 -0.0516 0.4337 0.5685
8.000 0.8005 0.04661 0.03782 -0.0521 0.4325 0.5724
8.250 0.8376 0.04595 0.03721 -0.0523 0.4314 0.5758
8.500 0.8807 0.04502 0.03630 -0.0532 0.4306 0.5799
10.500 0.6989 0.08572 0.07777 -0.0497 0.3583 0.5974
11.000 0.6882 0.09313 0.08536 -0.0502 0.3428 0.6026
11.250 0.7145 0.09309 0.08535 -0.0502 0.3411 0.6072
11.500 0.7437 0.09276 0.08504 -0.0503 0.3399 0.6122
12.000 0.7375 0.10006 0.09246 -0.0517 0.3243 0.6179
12.250 0.7641 0.09970 0.09218 -0.0512 0.3229 0.6217
13.000 0.7507 0.11134 0.10408 -0.0536 0.2982 0.6310
13.250 0.7659 0.11271 0.10548 -0.0541 0.2935 0.6358
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Polar data table (+)
Polar graphs
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