Falcon (falcon-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Falcon (falcon-il) Reynolds number: 200,000 Max Cl/Cd: 58.84 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-falcon-il-200000-n5.txt Download as CSV file: xf-falcon-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Falcon
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 -0.8388 0.06841 0.06396 -0.0427 1.0000 0.0202
-13.250 -0.8697 0.06027 0.05556 -0.0479 1.0000 0.0201
-13.000 -0.8933 0.05439 0.04942 -0.0503 1.0000 0.0202
-12.750 -0.9131 0.04977 0.04453 -0.0508 1.0000 0.0203
-12.500 -0.9285 0.04611 0.04060 -0.0500 1.0000 0.0205
-12.250 -0.9412 0.04306 0.03726 -0.0480 1.0000 0.0208
-12.000 -0.9504 0.04060 0.03449 -0.0452 1.0000 0.0211
-11.750 -0.9522 0.03880 0.03259 -0.0423 1.0000 0.0214
-11.500 -0.9505 0.03746 0.03119 -0.0394 1.0000 0.0218
-11.250 -0.9461 0.03633 0.02998 -0.0365 1.0000 0.0222
-11.000 -0.9392 0.03504 0.02858 -0.0341 1.0000 0.0226
-10.750 -0.9312 0.03370 0.02709 -0.0317 1.0000 0.0232
-10.500 -0.9219 0.03227 0.02549 -0.0293 1.0000 0.0237
-10.250 -0.9111 0.03084 0.02386 -0.0270 1.0000 0.0243
-10.000 -0.8987 0.02948 0.02230 -0.0248 1.0000 0.0250
-9.750 -0.8848 0.02823 0.02083 -0.0228 1.0000 0.0256
-9.500 -0.8705 0.02708 0.01959 -0.0209 1.0000 0.0264
-9.250 -0.8549 0.02623 0.01873 -0.0191 1.0000 0.0272
-9.000 -0.8386 0.02546 0.01790 -0.0174 1.0000 0.0281
-8.750 -0.8219 0.02462 0.01698 -0.0156 1.0000 0.0292
-8.500 -0.8050 0.02376 0.01600 -0.0138 1.0000 0.0302
-8.250 -0.7879 0.02293 0.01505 -0.0119 1.0000 0.0312
-8.000 -0.7724 0.02206 0.01415 -0.0099 1.0000 0.0322
-7.750 -0.7562 0.02144 0.01353 -0.0080 1.0000 0.0335
-7.500 -0.7400 0.02089 0.01294 -0.0060 1.0000 0.0350
-7.250 -0.7243 0.02033 0.01232 -0.0038 1.0000 0.0367
-6.750 -0.6716 0.01888 0.01080 -0.0041 0.9922 0.0407
-6.500 -0.6419 0.01825 0.01013 -0.0048 0.9813 0.0438
-6.250 -0.6100 0.01759 0.00945 -0.0059 0.9734 0.0475
-6.000 -0.5748 0.01700 0.00883 -0.0077 0.9675 0.0523
-5.750 -0.5401 0.01641 0.00824 -0.0093 0.9608 0.0577
-5.500 -0.5011 0.01590 0.00771 -0.0119 0.9555 0.0658
-5.250 -0.4644 0.01542 0.00724 -0.0139 0.9477 0.0753
-5.000 -0.4250 0.01495 0.00680 -0.0166 0.9405 0.0868
-4.750 -0.3899 0.01456 0.00642 -0.0183 0.9294 0.0984
-4.500 -0.3561 0.01420 0.00606 -0.0196 0.9169 0.1106
-4.250 -0.3240 0.01387 0.00573 -0.0206 0.9027 0.1236
-4.000 -0.2939 0.01356 0.00541 -0.0211 0.8868 0.1377
-3.750 -0.2658 0.01325 0.00511 -0.0211 0.8693 0.1540
-3.500 -0.2392 0.01290 0.00479 -0.0208 0.8505 0.1751
-3.000 -0.1979 0.01158 0.00413 -0.0182 0.8092 0.3484
-2.750 -0.1784 0.01109 0.00394 -0.0164 0.7875 0.4436
-2.500 -0.1574 0.01077 0.00378 -0.0148 0.7660 0.5108
-2.250 -0.1356 0.01054 0.00366 -0.0132 0.7445 0.5640
-2.000 -0.1134 0.01037 0.00357 -0.0117 0.7234 0.6122
-1.750 -0.0905 0.01026 0.00352 -0.0103 0.7036 0.6562
-1.500 -0.0667 0.01020 0.00348 -0.0090 0.6847 0.6979
-1.250 -0.0420 0.01019 0.00346 -0.0080 0.6665 0.7326
-1.000 -0.0166 0.01020 0.00346 -0.0071 0.6494 0.7643
-0.750 0.0100 0.01024 0.00347 -0.0065 0.6330 0.7910
-0.500 0.0370 0.01030 0.00348 -0.0060 0.6175 0.8162
0.000 0.0949 0.01047 0.00357 -0.0058 0.5878 0.8635
0.250 0.1272 0.01058 0.00362 -0.0064 0.5733 0.8814
0.500 0.1591 0.01069 0.00365 -0.0072 0.5592 0.8935
0.750 0.1933 0.01081 0.00369 -0.0084 0.5454 0.9031
1.000 0.2249 0.01092 0.00372 -0.0092 0.5322 0.9137
1.250 0.2607 0.01107 0.00378 -0.0108 0.5186 0.9220
1.500 0.2948 0.01121 0.00383 -0.0121 0.5050 0.9306
1.750 0.3310 0.01135 0.00392 -0.0139 0.4911 0.9383
2.000 0.3678 0.01151 0.00400 -0.0159 0.4772 0.9452
2.250 0.4057 0.01168 0.00411 -0.0180 0.4630 0.9513
2.500 0.4410 0.01185 0.00422 -0.0197 0.4490 0.9577
2.750 0.4780 0.01204 0.00434 -0.0217 0.4350 0.9622
3.000 0.5113 0.01223 0.00446 -0.0229 0.4217 0.9684
3.500 0.5811 0.01262 0.00474 -0.0262 0.3947 0.9783
3.750 0.6157 0.01281 0.00491 -0.0279 0.3820 0.9837
4.000 0.6487 0.01303 0.00508 -0.0292 0.3698 0.9905
4.250 0.6829 0.01326 0.00527 -0.0308 0.3578 0.9961
4.500 0.7190 0.01347 0.00545 -0.0328 0.3451 0.9999
4.750 0.7400 0.01361 0.00558 -0.0317 0.3348 1.0000
5.000 0.7601 0.01378 0.00573 -0.0303 0.3254 1.0000
5.250 0.7803 0.01397 0.00590 -0.0290 0.3152 1.0000
5.500 0.8008 0.01416 0.00609 -0.0277 0.3049 1.0000
5.750 0.8211 0.01439 0.00629 -0.0264 0.2952 1.0000
6.000 0.8418 0.01462 0.00652 -0.0251 0.2855 1.0000
6.250 0.8627 0.01487 0.00678 -0.0239 0.2762 1.0000
6.750 0.9042 0.01544 0.00734 -0.0214 0.2565 1.0000
7.000 0.9248 0.01575 0.00765 -0.0202 0.2470 1.0000
7.250 0.9452 0.01609 0.00799 -0.0189 0.2378 1.0000
7.500 0.9661 0.01642 0.00835 -0.0178 0.2295 1.0000
7.750 0.9859 0.01682 0.00873 -0.0164 0.2216 1.0000
8.000 1.0067 0.01717 0.00914 -0.0152 0.2138 1.0000
8.250 1.0256 0.01762 0.00957 -0.0138 0.2059 1.0000
8.500 1.0456 0.01800 0.01000 -0.0125 0.1963 1.0000
8.750 1.0643 0.01846 0.01045 -0.0111 0.1866 1.0000
9.000 1.0816 0.01898 0.01094 -0.0095 0.1768 1.0000
9.250 1.1007 0.01941 0.01143 -0.0082 0.1678 1.0000
9.500 1.1180 0.01993 0.01196 -0.0066 0.1597 1.0000
9.750 1.1350 0.02046 0.01250 -0.0051 0.1509 1.0000
10.000 1.1520 0.02098 0.01307 -0.0035 0.1433 1.0000
10.250 1.1664 0.02162 0.01371 -0.0016 0.1345 1.0000
10.500 1.1824 0.02217 0.01432 0.0001 0.1249 1.0000
10.750 1.1962 0.02282 0.01500 0.0020 0.1159 1.0000
11.000 1.2070 0.02358 0.01575 0.0044 0.1030 1.0000
11.250 1.2124 0.02450 0.01662 0.0075 0.0858 1.0000
11.750 1.1976 0.02815 0.01989 0.0155 0.0364 1.0000
12.000 1.1945 0.03004 0.02179 0.0182 0.0304 1.0000
12.250 1.1953 0.03182 0.02365 0.0201 0.0275 1.0000
12.500 1.1943 0.03390 0.02583 0.0217 0.0256 1.0000
12.750 1.1947 0.03605 0.02809 0.0227 0.0243 1.0000
13.000 1.1948 0.03840 0.03059 0.0234 0.0233 1.0000
13.250 1.1927 0.04115 0.03347 0.0237 0.0224 1.0000
13.500 1.1887 0.04431 0.03676 0.0235 0.0217 1.0000
13.750 1.1826 0.04790 0.04049 0.0229 0.0212 1.0000
14.000 1.1733 0.05205 0.04478 0.0220 0.0208 1.0000
14.250 1.1625 0.05659 0.04946 0.0207 0.0204 1.0000
14.500 1.1541 0.06091 0.05393 0.0194 0.0201 1.0000
14.750 1.1438 0.06562 0.05878 0.0178 0.0198 1.0000
15.000 1.1325 0.07055 0.06386 0.0161 0.0196 1.0000
15.250 1.1203 0.07580 0.06925 0.0142 0.0193 1.0000
15.500 1.1079 0.08121 0.07478 0.0121 0.0191 1.0000
15.750 1.0953 0.08677 0.08047 0.0100 0.0188 1.0000
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