FX 75-VG-166/22 (fx75vg166-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 75-VG-166/22 (fx75vg166-il) Reynolds number: 200,000 Max Cl/Cd: 44.99 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx75vg166-il-200000-n5.txt Download as CSV file: xf-fx75vg166-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 75-VG-166/22
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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4164 0.07837 0.07332 -0.1033 0.7682 0.0156
-13.250 -0.4508 0.06868 0.06346 -0.1097 0.7679 0.0155
-13.000 -0.4705 0.06329 0.05794 -0.1124 0.7673 0.0154
-12.750 -0.4986 0.05778 0.05220 -0.1138 0.7667 0.0154
-12.500 -0.5203 0.05362 0.04783 -0.1136 0.7659 0.0154
-12.250 -0.5389 0.05003 0.04404 -0.1124 0.7650 0.0154
-12.000 -0.5502 0.04727 0.04108 -0.1107 0.7641 0.0153
-11.750 -0.5703 0.04371 0.03717 -0.1077 0.7629 0.0155
-11.500 -0.5774 0.04131 0.03451 -0.1052 0.7617 0.0156
-11.250 -0.5808 0.03911 0.03201 -0.1027 0.7605 0.0157
-11.000 -0.5786 0.03727 0.03002 -0.1005 0.7596 0.0160
-10.750 -0.5715 0.03622 0.02891 -0.0988 0.7586 0.0165
-10.500 -0.5633 0.03445 0.02691 -0.0969 0.7575 0.0165
-10.250 -0.5542 0.03368 0.02606 -0.0951 0.7565 0.0172
-10.000 -0.5440 0.03279 0.02503 -0.0932 0.7554 0.0180
-9.750 -0.5300 0.03146 0.02346 -0.0917 0.7545 0.0186
-9.500 -0.5126 0.03006 0.02175 -0.0905 0.7537 0.0194
-9.250 -0.4923 0.02890 0.02048 -0.0899 0.7531 0.0201
-9.000 -0.4730 0.02802 0.01957 -0.0891 0.7521 0.0207
-8.750 -0.4532 0.02723 0.01872 -0.0884 0.7511 0.0215
-8.500 -0.4319 0.02643 0.01785 -0.0877 0.7500 0.0222
-8.250 -0.4106 0.02570 0.01701 -0.0870 0.7489 0.0234
-8.000 -0.3909 0.02506 0.01632 -0.0861 0.7478 0.0249
-7.750 -0.3724 0.02454 0.01581 -0.0851 0.7467 0.0262
-7.500 -0.3531 0.02397 0.01520 -0.0840 0.7456 0.0276
-7.250 -0.3343 0.02344 0.01460 -0.0828 0.7445 0.0290
-7.000 -0.3174 0.02290 0.01403 -0.0814 0.7433 0.0302
-6.750 -0.3007 0.02249 0.01362 -0.0800 0.7422 0.0324
-6.500 -0.2839 0.02210 0.01318 -0.0784 0.7411 0.0346
-6.250 -0.2688 0.02168 0.01271 -0.0765 0.7401 0.0366
-6.000 -0.2545 0.02131 0.01233 -0.0746 0.7392 0.0391
-5.750 -0.2396 0.02107 0.01206 -0.0727 0.7380 0.0429
-5.500 -0.2260 0.02078 0.01182 -0.0706 0.7363 0.0470
-5.250 -0.2097 0.02056 0.01160 -0.0690 0.7346 0.0526
-5.000 -0.1938 0.02029 0.01138 -0.0673 0.7330 0.0630
-4.750 -0.1778 0.02000 0.01117 -0.0656 0.7315 0.0791
-4.500 -0.1627 0.01962 0.01095 -0.0639 0.7300 0.1113
-4.250 -0.1494 0.01911 0.01071 -0.0618 0.7285 0.1713
-4.000 -0.1396 0.01843 0.01045 -0.0593 0.7272 0.2625
-3.750 -0.1342 0.01756 0.01016 -0.0561 0.7260 0.3920
-3.500 -0.1294 0.01670 0.01012 -0.0521 0.7249 0.5566
-3.250 -0.0897 0.01894 0.01299 -0.0497 0.7242 0.6869
-3.000 -0.0765 0.01926 0.01329 -0.0476 0.7204 0.7164
-2.750 -0.0533 0.01990 0.01387 -0.0465 0.7182 0.7376
-2.500 -0.0296 0.02068 0.01458 -0.0453 0.7164 0.7582
-2.250 -0.0100 0.02123 0.01505 -0.0437 0.7149 0.7768
-2.000 0.0203 0.02189 0.01565 -0.0431 0.7139 0.7821
-1.750 0.0410 0.02199 0.01567 -0.0421 0.7127 0.7909
-1.500 0.0691 0.02218 0.01580 -0.0419 0.7118 0.7933
-1.250 0.0966 0.02230 0.01585 -0.0416 0.7110 0.7965
-1.000 0.1066 0.02263 0.01620 -0.0393 0.7062 0.8032
-0.750 0.1260 0.02274 0.01627 -0.0382 0.7037 0.8066
-0.500 0.1498 0.02285 0.01636 -0.0376 0.7020 0.8086
-0.250 0.1742 0.02290 0.01637 -0.0371 0.7005 0.8114
0.000 0.1987 0.02284 0.01627 -0.0367 0.6992 0.8145
0.250 0.2233 0.02268 0.01604 -0.0366 0.6980 0.8184
0.500 0.2498 0.02251 0.01582 -0.0366 0.6970 0.8208
0.750 0.2556 0.02304 0.01643 -0.0335 0.6896 0.8228
1.000 0.2788 0.02305 0.01643 -0.0330 0.6876 0.8246
1.250 0.3034 0.02301 0.01638 -0.0327 0.6861 0.8265
1.500 0.3296 0.02290 0.01625 -0.0326 0.6849 0.8287
1.750 0.3569 0.02275 0.01607 -0.0328 0.6838 0.8309
2.250 0.3830 0.02331 0.01671 -0.0292 0.6736 0.8362
2.500 0.4109 0.02307 0.01647 -0.0293 0.6718 0.8370
2.750 0.4399 0.02282 0.01622 -0.0296 0.6705 0.8379
3.000 0.4687 0.02261 0.01603 -0.0299 0.6695 0.8388
3.500 0.4914 0.02331 0.01682 -0.0259 0.6578 0.8422
3.750 0.5219 0.02298 0.01651 -0.0264 0.6562 0.8431
4.000 0.5541 0.02256 0.01612 -0.0271 0.6550 0.8442
4.250 0.5864 0.02214 0.01573 -0.0279 0.6540 0.8454
4.750 0.6119 0.02267 0.01635 -0.0244 0.6409 0.8486
5.000 0.6441 0.02220 0.01594 -0.0251 0.6397 0.8493
5.500 0.6629 0.02230 0.01616 -0.0194 0.6260 0.8522
6.000 0.6980 0.02188 0.01585 -0.0163 0.6110 0.8548
6.250 0.7022 0.02243 0.01644 -0.0134 0.5986 0.8561
6.500 0.7452 0.02121 0.01526 -0.0150 0.5938 0.8564
6.750 0.7462 0.02211 0.01621 -0.0119 0.5799 0.8577
7.000 0.7588 0.02251 0.01666 -0.0103 0.5677 0.8587
7.250 0.7854 0.02219 0.01639 -0.0101 0.5573 0.8594
7.500 0.8230 0.02130 0.01552 -0.0110 0.5452 0.8598
7.750 0.8574 0.02057 0.01479 -0.0114 0.5273 0.8602
8.000 0.8877 0.01999 0.01411 -0.0113 0.4979 0.8608
8.250 0.9033 0.02008 0.01392 -0.0093 0.4533 0.8620
8.500 0.9053 0.02094 0.01455 -0.0061 0.4139 0.8631
8.750 0.9048 0.02204 0.01545 -0.0030 0.3781 0.8640
9.250 0.8929 0.02489 0.01781 0.0040 0.2982 0.8655
9.500 0.8891 0.02636 0.01907 0.0070 0.2594 0.8662
9.750 0.8890 0.02775 0.02028 0.0094 0.2271 0.8668
10.000 0.8904 0.02915 0.02152 0.0115 0.1978 0.8673
10.250 0.8974 0.03033 0.02262 0.0129 0.1757 0.8678
10.500 0.9037 0.03162 0.02382 0.0142 0.1551 0.8683
10.750 0.9125 0.03282 0.02496 0.0153 0.1374 0.8687
11.000 0.9219 0.03406 0.02614 0.0162 0.1192 0.8690
11.250 0.9319 0.03531 0.02736 0.0169 0.1050 0.8694
11.500 0.9415 0.03661 0.02862 0.0177 0.0892 0.8698
11.750 0.9490 0.03810 0.03001 0.0185 0.0717 0.8701
12.000 0.9576 0.03957 0.03144 0.0193 0.0595 0.8704
12.250 0.9663 0.04108 0.03292 0.0199 0.0497 0.8708
12.500 0.9748 0.04264 0.03447 0.0205 0.0429 0.8713
12.750 0.9834 0.04424 0.03609 0.0210 0.0378 0.8717
13.000 0.9924 0.04583 0.03773 0.0214 0.0348 0.8723
13.250 1.0001 0.04756 0.03952 0.0218 0.0321 0.8727
13.500 1.0084 0.04929 0.04135 0.0222 0.0304 0.8730
13.750 1.0152 0.05120 0.04329 0.0224 0.0278 0.8732
14.000 1.0218 0.05319 0.04535 0.0226 0.0267 0.8735
14.250 1.0289 0.05517 0.04745 0.0228 0.0257 0.8740
14.500 1.0351 0.05730 0.04967 0.0228 0.0246 0.8745
14.750 1.0409 0.05950 0.05196 0.0228 0.0234 0.8753
15.000 1.0453 0.06188 0.05441 0.0227 0.0228 0.8757
15.250 1.0479 0.06452 0.05710 0.0226 0.0221 0.8760
15.500 1.0536 0.06687 0.05958 0.0223 0.0214 0.8761
15.750 1.0590 0.06932 0.06215 0.0220 0.0209 0.8762
16.000 1.0639 0.07186 0.06480 0.0216 0.0201 0.8763
16.250 1.0688 0.07445 0.06749 0.0210 0.0195 0.8764
16.500 1.0714 0.07739 0.07050 0.0202 0.0185 0.8765
16.750 1.0744 0.08027 0.07346 0.0196 0.0182 0.8766
17.000 1.0773 0.08314 0.07639 0.0189 0.0179 0.8767
17.250 1.0806 0.08611 0.07950 0.0182 0.0174 0.8768
17.500 1.0844 0.08900 0.08251 0.0174 0.0173 0.8769
17.750 1.0864 0.09223 0.08592 0.0163 0.0169 0.8771
18.000 1.0876 0.09562 0.08945 0.0152 0.0165 0.8772
18.250 1.0887 0.09907 0.09305 0.0139 0.0163 0.8773
18.500 1.0885 0.10279 0.09692 0.0125 0.0159 0.8774
18.750 1.0882 0.10655 0.10083 0.0109 0.0158 0.8775
19.000 1.0855 0.11077 0.10520 0.0090 0.0155 0.8776
19.250 1.0825 0.11510 0.10967 0.0069 0.0153 0.8777
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