FX 75-VG-166/22 (fx75vg166-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: FX 75-VG-166/22 (fx75vg166-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.76 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx75vg166-il-1000000.txt Download as CSV file: xf-fx75vg166-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6691 0.06785 0.06444 -0.0986 0.7446 0.0093
-15.500 -0.4605 0.06794 0.06485 -0.1012 0.7423 0.0108
-15.250 -0.7505 0.04824 0.04412 -0.1102 0.7440 0.0091
-15.000 -0.6759 0.05453 0.05085 -0.1096 0.7434 0.0099
-14.750 -0.7267 0.04523 0.04110 -0.1129 0.7431 0.0096
-14.500 -0.7561 0.03942 0.03491 -0.1131 0.7426 0.0093
-14.250 -0.7230 0.04044 0.03609 -0.1144 0.7420 0.0099
-14.000 -0.7399 0.03616 0.03149 -0.1138 0.7415 0.0097
-13.750 -0.7399 0.03360 0.02873 -0.1135 0.7408 0.0097
-13.500 -0.7197 0.03323 0.02836 -0.1143 0.7400 0.0101
-13.250 -0.7163 0.03139 0.02637 -0.1131 0.7397 0.0103
-13.000 -0.7070 0.03023 0.02510 -0.1121 0.7393 0.0105
-12.750 -0.6985 0.02884 0.02359 -0.1109 0.7387 0.0105
-12.500 -0.6896 0.02741 0.02202 -0.1096 0.7380 0.0107
-12.250 -0.6785 0.02610 0.02058 -0.1084 0.7374 0.0107
-12.000 -0.6632 0.02540 0.01980 -0.1075 0.7367 0.0110
-11.750 -0.6504 0.02408 0.01837 -0.1063 0.7359 0.0109
-11.500 -0.6331 0.02360 0.01782 -0.1056 0.7352 0.0111
-11.250 -0.6196 0.02230 0.01638 -0.1043 0.7344 0.0115
-11.000 -0.6004 0.02190 0.01594 -0.1036 0.7336 0.0112
-10.750 -0.5874 0.02067 0.01466 -0.1022 0.7329 0.0120
-10.500 -0.5700 0.02004 0.01399 -0.1012 0.7322 0.0123
-10.250 -0.5526 0.01939 0.01329 -0.1001 0.7316 0.0124
-10.000 -0.5328 0.01900 0.01288 -0.0994 0.7309 0.0128
-9.750 -0.5144 0.01846 0.01229 -0.0983 0.7303 0.0131
-9.500 -0.4954 0.01800 0.01177 -0.0974 0.7296 0.0136
-9.250 -0.4764 0.01753 0.01126 -0.0964 0.7290 0.0139
-9.000 -0.4592 0.01696 0.01064 -0.0951 0.7284 0.0146
-8.750 -0.4419 0.01645 0.01011 -0.0938 0.7277 0.0153
-8.500 -0.4219 0.01613 0.00978 -0.0929 0.7270 0.0160
-8.250 -0.4029 0.01578 0.00940 -0.0918 0.7263 0.0164
-8.000 -0.3824 0.01558 0.00918 -0.0909 0.7253 0.0172
-7.750 -0.3656 0.01522 0.00878 -0.0893 0.7244 0.0180
-7.500 -0.3499 0.01470 0.00827 -0.0876 0.7239 0.0190
-7.250 -0.3318 0.01436 0.00792 -0.0862 0.7233 0.0196
-7.000 -0.3128 0.01406 0.00763 -0.0849 0.7226 0.0208
-6.750 -0.2948 0.01375 0.00729 -0.0834 0.7217 0.0215
-6.500 -0.2799 0.01336 0.00690 -0.0813 0.7207 0.0232
-6.250 -0.2634 0.01311 0.00666 -0.0795 0.7198 0.0244
-6.000 -0.2461 0.01293 0.00647 -0.0778 0.7189 0.0259
-5.750 -0.2310 0.01271 0.00624 -0.0757 0.7179 0.0278
-5.500 -0.2136 0.01251 0.00606 -0.0739 0.7170 0.0302
-5.250 -0.1935 0.01232 0.00586 -0.0726 0.7161 0.0334
-5.000 -0.1734 0.01210 0.00566 -0.0714 0.7153 0.0382
-4.750 -0.1533 0.01186 0.00546 -0.0702 0.7145 0.0464
-4.500 -0.1340 0.01157 0.00527 -0.0689 0.7137 0.0658
-4.250 -0.1152 0.01124 0.00508 -0.0675 0.7130 0.0985
-4.000 -0.0981 0.01083 0.00488 -0.0658 0.7122 0.1537
-3.750 -0.0819 0.01037 0.00469 -0.0640 0.7113 0.2250
-3.500 -0.0685 0.00983 0.00452 -0.0618 0.7102 0.3241
-3.250 -0.0585 0.00908 0.00428 -0.0590 0.7088 0.4535
-3.000 -0.0481 0.00824 0.00393 -0.0561 0.7077 0.5837
-2.750 -0.0346 0.00775 0.00393 -0.0532 0.7064 0.7059
-2.500 -0.0064 0.00802 0.00431 -0.0531 0.7053 0.7373
-2.250 0.0230 0.00823 0.00449 -0.0534 0.7042 0.7506
-2.000 0.0524 0.00846 0.00469 -0.0538 0.7031 0.7613
-1.750 0.0821 0.00872 0.00492 -0.0541 0.7021 0.7689
-1.500 0.1133 0.00907 0.00527 -0.0546 0.7010 0.7737
-1.250 0.1428 0.00936 0.00552 -0.0549 0.7000 0.7806
-1.000 0.1738 0.00965 0.00584 -0.0553 0.6992 0.7833
-0.750 0.2048 0.00996 0.00615 -0.0557 0.6984 0.7858
-0.500 0.2350 0.01012 0.00631 -0.0561 0.6975 0.7879
-0.250 0.2646 0.01018 0.00634 -0.0565 0.6967 0.7900
0.000 0.2939 0.01023 0.00635 -0.0570 0.6956 0.7927
0.250 0.3222 0.01033 0.00640 -0.0574 0.6944 0.7955
0.500 0.3486 0.01020 0.00631 -0.0572 0.6929 0.7967
0.750 0.3759 0.01016 0.00629 -0.0572 0.6912 0.7976
1.000 0.4038 0.01011 0.00626 -0.0574 0.6895 0.7984
1.250 0.4322 0.01008 0.00624 -0.0576 0.6879 0.7994
1.500 0.4609 0.01005 0.00621 -0.0578 0.6864 0.8004
1.750 0.4900 0.00998 0.00614 -0.0582 0.6850 0.8014
2.000 0.5194 0.00985 0.00600 -0.0587 0.6835 0.8024
2.250 0.5487 0.00973 0.00586 -0.0592 0.6821 0.8033
2.500 0.5777 0.00967 0.00579 -0.0596 0.6803 0.8043
2.750 0.6039 0.00960 0.00577 -0.0595 0.6780 0.8056
3.000 0.6312 0.00955 0.00573 -0.0597 0.6757 0.8071
3.250 0.6596 0.00937 0.00556 -0.0600 0.6723 0.8083
3.500 0.6887 0.00913 0.00529 -0.0604 0.6683 0.8093
3.750 0.7161 0.00902 0.00518 -0.0604 0.6625 0.8103
4.000 0.7419 0.00884 0.00503 -0.0602 0.6577 0.8113
4.250 0.7685 0.00870 0.00490 -0.0602 0.6540 0.8121
4.500 0.7951 0.00863 0.00485 -0.0601 0.6499 0.8127
4.750 0.8212 0.00857 0.00485 -0.0600 0.6438 0.8133
5.000 0.8472 0.00850 0.00477 -0.0597 0.6373 0.8139
5.250 0.8729 0.00848 0.00479 -0.0595 0.6283 0.8146
5.500 0.8974 0.00847 0.00478 -0.0590 0.6174 0.8152
5.750 0.9192 0.00853 0.00479 -0.0579 0.5991 0.8160
6.000 0.9374 0.00870 0.00487 -0.0562 0.5705 0.8170
6.250 0.9482 0.00908 0.00509 -0.0529 0.5319 0.8184
6.500 0.9542 0.00957 0.00541 -0.0489 0.4884 0.8199
6.750 0.9560 0.01012 0.00578 -0.0441 0.4494 0.8212
7.000 0.9545 0.01062 0.00613 -0.0387 0.4152 0.8225
7.250 0.9431 0.01116 0.00653 -0.0313 0.3829 0.8239
7.500 0.9332 0.01191 0.00715 -0.0246 0.3538 0.8250
7.750 0.9185 0.01282 0.00795 -0.0176 0.3257 0.8266
8.000 0.9085 0.01419 0.00924 -0.0128 0.3026 0.8278
8.250 0.9005 0.01546 0.01038 -0.0081 0.2737 0.8287
8.500 0.8919 0.01680 0.01154 -0.0035 0.2384 0.8296
8.750 0.8894 0.01799 0.01255 0.0001 0.2060 0.8303
9.000 0.8971 0.01883 0.01332 0.0021 0.1873 0.8309
9.250 0.9011 0.01987 0.01421 0.0046 0.1604 0.8315
9.500 0.9086 0.02083 0.01506 0.0064 0.1381 0.8319
9.750 0.9208 0.02161 0.01579 0.0076 0.1251 0.8323
10.000 0.9328 0.02244 0.01654 0.0088 0.1097 0.8327
10.250 0.9441 0.02334 0.01735 0.0100 0.0932 0.8331
10.500 0.9551 0.02431 0.01823 0.0110 0.0778 0.8334
10.750 0.9669 0.02527 0.01912 0.0119 0.0630 0.8337
11.000 0.9760 0.02645 0.02018 0.0130 0.0457 0.8340
11.250 0.9892 0.02747 0.02115 0.0136 0.0368 0.8342
11.500 1.0025 0.02853 0.02219 0.0141 0.0309 0.8344
11.750 1.0165 0.02958 0.02321 0.0144 0.0259 0.8346
12.000 1.0336 0.03046 0.02412 0.0145 0.0246 0.8348
12.250 1.0478 0.03155 0.02521 0.0147 0.0224 0.8350
12.500 1.0618 0.03271 0.02640 0.0149 0.0211 0.8351
12.750 1.0785 0.03369 0.02742 0.0149 0.0199 0.8353
13.000 1.0935 0.03483 0.02858 0.0149 0.0187 0.8354
13.250 1.1035 0.03637 0.03016 0.0152 0.0174 0.8355
13.500 1.1191 0.03747 0.03131 0.0151 0.0166 0.8357
13.750 1.1337 0.03867 0.03256 0.0151 0.0160 0.8359
14.000 1.1473 0.04001 0.03394 0.0150 0.0153 0.8361
14.250 1.1598 0.04146 0.03544 0.0150 0.0149 0.8362
14.500 1.1670 0.04335 0.03738 0.0152 0.0140 0.8363
14.750 1.1757 0.04519 0.03928 0.0152 0.0135 0.8364
15.000 1.1908 0.04652 0.04067 0.0148 0.0131 0.8364
15.250 1.1995 0.04843 0.04265 0.0147 0.0130 0.8364
15.500 1.2123 0.05001 0.04427 0.0143 0.0124 0.8365
15.750 1.2226 0.05179 0.04612 0.0141 0.0121 0.8366
16.000 1.2323 0.05369 0.04807 0.0137 0.0117 0.8366
16.250 1.2388 0.05588 0.05033 0.0135 0.0117 0.8368
16.500 1.2332 0.05935 0.05387 0.0136 0.0109 0.8368
16.750 1.2439 0.06121 0.05579 0.0131 0.0111 0.8370
17.000 1.2374 0.06483 0.05952 0.0131 0.0108 0.8371
17.250 1.2477 0.06685 0.06161 0.0124 0.0105 0.8372
17.500 1.2492 0.06982 0.06466 0.0118 0.0106 0.8372
17.750 1.2538 0.07252 0.06746 0.0111 0.0104 0.8371
18.000 1.2571 0.07543 0.07045 0.0103 0.0102 0.8371
18.250 1.2587 0.07853 0.07365 0.0095 0.0101 0.8370
18.500 1.2613 0.08156 0.07675 0.0085 0.0099 0.8370
18.750 1.2660 0.08444 0.07970 0.0074 0.0096 0.8369
19.000 1.2610 0.08845 0.08382 0.0063 0.0096 0.8369
19.250 1.2627 0.09179 0.08722 0.0050 0.0094 0.8368
|
Polar data table (+)
Polar graphs
<< Back to FX 75-VG-166/22 (fx75vg166-il)