AH 85-L-120/17 (ah85l120-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AH 85-L-120/17 (ah85l120-il) Reynolds number: 200,000 Max Cl/Cd: 34.99 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ah85l120-il-200000-n5.txt Download as CSV file: xf-ah85l120-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AH 85-L-120/17
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6579 0.08635 0.08286 -0.0364 1.0000 0.0117
-12.000 -0.6769 0.07772 0.07414 -0.0428 1.0000 0.0114
-11.750 -0.6981 0.07075 0.06705 -0.0472 1.0000 0.0111
-11.500 -0.7196 0.06493 0.06110 -0.0496 1.0000 0.0112
-11.250 -0.7402 0.06009 0.05610 -0.0502 1.0000 0.0111
-11.000 -0.7611 0.05569 0.05150 -0.0495 1.0000 0.0110
-10.750 -0.7788 0.05197 0.04756 -0.0477 1.0000 0.0112
-10.500 -0.7930 0.04885 0.04423 -0.0451 1.0000 0.0111
-10.250 -0.8068 0.04599 0.04115 -0.0416 1.0000 0.0110
-10.000 -0.8214 0.04357 0.03848 -0.0369 1.0000 0.0113
-9.750 -0.8145 0.04019 0.03466 -0.0363 0.9780 0.0115
-9.500 -0.8002 0.03767 0.03161 -0.0361 0.9692 0.0124
-9.250 -0.7870 0.03414 0.02760 -0.0356 0.9633 0.0128
-9.000 -0.7660 0.03150 0.02460 -0.0359 0.9593 0.0129
-8.750 -0.7429 0.02867 0.02148 -0.0364 0.9563 0.0135
-8.500 -0.7187 0.02695 0.01955 -0.0366 0.9525 0.0139
-8.250 -0.6927 0.02542 0.01784 -0.0371 0.9491 0.0145
-8.000 -0.6649 0.02395 0.01619 -0.0377 0.9463 0.0151
-7.750 -0.6371 0.02277 0.01482 -0.0384 0.9438 0.0165
-7.500 -0.6111 0.02171 0.01364 -0.0386 0.9411 0.0174
-7.250 -0.5871 0.02090 0.01271 -0.0384 0.9378 0.0186
-7.000 -0.5660 0.01966 0.01139 -0.0378 0.9344 0.0197
-6.750 -0.5459 0.01869 0.01035 -0.0370 0.9309 0.0208
-6.500 -0.5260 0.01798 0.00957 -0.0361 0.9278 0.0225
-6.250 -0.5087 0.01742 0.00889 -0.0345 0.9241 0.0253
-6.000 -0.4892 0.01697 0.00835 -0.0333 0.9206 0.0277
-5.750 -0.4711 0.01635 0.00769 -0.0319 0.9173 0.0339
-5.500 -0.4520 0.01582 0.00714 -0.0306 0.9145 0.0443
-5.250 -0.4378 0.01523 0.00671 -0.0285 0.9107 0.0747
-5.000 -0.4256 0.01448 0.00631 -0.0261 0.9068 0.1432
-4.750 -0.4139 0.01369 0.00590 -0.0237 0.9034 0.2333
-4.500 -0.4062 0.01283 0.00555 -0.0205 0.9000 0.3450
-4.250 -0.4052 0.01197 0.00532 -0.0157 0.8950 0.4772
-4.000 -0.3967 0.01136 0.00540 -0.0117 0.8915 0.6152
-3.750 -0.3711 0.01155 0.00595 -0.0103 0.8895 0.7061
-3.500 -0.3449 0.01180 0.00616 -0.0096 0.8876 0.7354
-3.250 -0.3216 0.01202 0.00629 -0.0084 0.8846 0.7528
-3.000 -0.2988 0.01223 0.00643 -0.0073 0.8813 0.7675
-2.750 -0.2745 0.01243 0.00656 -0.0064 0.8784 0.7793
-2.500 -0.2499 0.01264 0.00669 -0.0055 0.8759 0.7909
-2.250 -0.2262 0.01280 0.00676 -0.0045 0.8736 0.8021
-2.000 -0.1982 0.01306 0.00699 -0.0043 0.8707 0.8078
-1.750 -0.1779 0.01310 0.00697 -0.0029 0.8666 0.8151
-1.500 -0.1508 0.01317 0.00700 -0.0028 0.8637 0.8191
-1.250 -0.1229 0.01323 0.00701 -0.0027 0.8612 0.8229
-1.000 -0.0979 0.01321 0.00693 -0.0023 0.8588 0.8283
-0.750 -0.0766 0.01326 0.00697 -0.0011 0.8538 0.8326
-0.500 -0.0499 0.01330 0.00701 -0.0009 0.8503 0.8357
-0.250 -0.0237 0.01329 0.00698 -0.0007 0.8474 0.8396
0.000 0.0000 0.01322 0.00686 0.0000 0.8449 0.8449
0.250 0.0237 0.01330 0.00698 0.0007 0.8397 0.8474
0.500 0.0499 0.01330 0.00701 0.0010 0.8357 0.8504
0.750 0.0765 0.01326 0.00698 0.0012 0.8326 0.8539
1.000 0.0982 0.01321 0.00693 0.0022 0.8284 0.8587
1.250 0.1229 0.01323 0.00701 0.0027 0.8230 0.8612
1.500 0.1509 0.01317 0.00700 0.0028 0.8191 0.8637
1.750 0.1778 0.01310 0.00697 0.0030 0.8151 0.8667
2.000 0.1983 0.01304 0.00697 0.0043 0.8074 0.8706
2.250 0.2263 0.01279 0.00675 0.0045 0.8021 0.8735
2.500 0.2500 0.01264 0.00669 0.0055 0.7909 0.8758
2.750 0.2746 0.01244 0.00658 0.0064 0.7797 0.8785
3.000 0.2988 0.01223 0.00643 0.0073 0.7675 0.8814
3.250 0.3216 0.01203 0.00630 0.0085 0.7532 0.8847
3.500 0.3449 0.01180 0.00616 0.0096 0.7353 0.8876
3.750 0.3709 0.01157 0.00598 0.0103 0.7077 0.8895
4.000 0.3971 0.01135 0.00544 0.0116 0.6228 0.8915
4.250 0.4060 0.01194 0.00533 0.0156 0.4818 0.8950
4.500 0.4074 0.01279 0.00555 0.0203 0.3512 0.8999
4.750 0.4137 0.01369 0.00590 0.0237 0.2329 0.9034
5.000 0.4258 0.01446 0.00630 0.0261 0.1453 0.9068
5.250 0.4368 0.01529 0.00673 0.0286 0.0682 0.9109
5.500 0.4521 0.01581 0.00714 0.0306 0.0443 0.9145
5.750 0.4711 0.01635 0.00770 0.0319 0.0340 0.9173
6.000 0.4890 0.01699 0.00836 0.0334 0.0276 0.9206
6.250 0.5085 0.01744 0.00892 0.0346 0.0243 0.9241
6.500 0.5259 0.01798 0.00957 0.0362 0.0226 0.9278
6.750 0.5460 0.01867 0.01035 0.0371 0.0212 0.9310
7.000 0.5650 0.01981 0.01154 0.0380 0.0193 0.9345
7.250 0.5870 0.02096 0.01277 0.0384 0.0186 0.9378
7.500 0.6110 0.02167 0.01360 0.0386 0.0172 0.9412
7.750 0.6369 0.02268 0.01474 0.0384 0.0162 0.9439
8.000 0.6647 0.02397 0.01621 0.0378 0.0148 0.9464
8.250 0.6920 0.02536 0.01775 0.0372 0.0141 0.9493
8.500 0.7183 0.02695 0.01953 0.0367 0.0137 0.9526
8.750 0.7419 0.02897 0.02174 0.0364 0.0131 0.9563
9.000 0.7649 0.03201 0.02514 0.0360 0.0127 0.9593
9.250 0.7853 0.03473 0.02824 0.0358 0.0127 0.9633
9.500 0.7988 0.03832 0.03227 0.0361 0.0126 0.9691
9.750 0.8114 0.04098 0.03543 0.0364 0.0121 0.9782
10.000 0.8153 0.04435 0.03923 0.0375 0.0118 1.0000
10.250 0.8050 0.04622 0.04137 0.0418 0.0112 1.0000
10.500 0.7904 0.04914 0.04454 0.0453 0.0111 1.0000
10.750 0.7745 0.05249 0.04811 0.0479 0.0110 1.0000
11.000 0.7600 0.05583 0.05162 0.0495 0.0113 1.0000
11.250 0.7369 0.06059 0.05661 0.0502 0.0110 1.0000
11.500 0.7187 0.06514 0.06128 0.0495 0.0111 1.0000
11.750 0.6969 0.07099 0.06729 0.0470 0.0112 1.0000
12.000 0.6748 0.07817 0.07457 0.0424 0.0116 1.0000
12.250 0.6619 0.08423 0.08065 0.0383 0.0123 1.0000
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