Falcon (falcon-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Falcon (falcon-il) Reynolds number: 500,000 Max Cl/Cd: 81.78 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-falcon-il-500000.txt Download as CSV file: xf-falcon-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.9315 0.06645 0.06322 -0.0431 1.0000 0.0179
-14.250 -0.9597 0.05868 0.05521 -0.0479 1.0000 0.0178
-14.000 -0.9818 0.05276 0.04908 -0.0506 1.0000 0.0178
-13.750 -0.9948 0.04868 0.04483 -0.0515 1.0000 0.0179
-13.500 -1.0052 0.04527 0.04126 -0.0514 1.0000 0.0180
-13.250 -1.0107 0.04272 0.03859 -0.0506 1.0000 0.0182
-13.000 -1.0165 0.04034 0.03606 -0.0491 1.0000 0.0184
-12.750 -1.0207 0.03830 0.03389 -0.0470 1.0000 0.0186
-12.500 -1.0239 0.03649 0.03193 -0.0443 1.0000 0.0188
-12.250 -1.0245 0.03503 0.03036 -0.0412 1.0000 0.0191
-12.000 -1.0252 0.03370 0.02889 -0.0376 1.0000 0.0194
-11.750 -1.0232 0.03246 0.02751 -0.0342 1.0000 0.0198
-11.500 -1.0168 0.03112 0.02601 -0.0314 1.0000 0.0202
-11.250 -1.0083 0.02990 0.02461 -0.0288 1.0000 0.0206
-11.000 -0.9976 0.02883 0.02337 -0.0263 1.0000 0.0210
-10.750 -0.9884 0.02710 0.02142 -0.0238 1.0000 0.0213
-10.500 -0.9771 0.02529 0.01952 -0.0216 1.0000 0.0219
-10.250 -0.9617 0.02435 0.01854 -0.0198 1.0000 0.0224
-10.000 -0.9452 0.02357 0.01771 -0.0181 1.0000 0.0230
-9.750 -0.9283 0.02278 0.01685 -0.0163 1.0000 0.0236
-9.500 -0.9109 0.02201 0.01599 -0.0146 1.0000 0.0243
-9.250 -0.8931 0.02126 0.01514 -0.0129 1.0000 0.0249
-9.000 -0.8744 0.02073 0.01451 -0.0112 1.0000 0.0256
-8.750 -0.8593 0.01954 0.01325 -0.0091 1.0000 0.0265
-8.500 -0.8437 0.01877 0.01247 -0.0070 1.0000 0.0274
-8.250 -0.8279 0.01826 0.01195 -0.0049 1.0000 0.0282
-8.000 -0.8138 0.01779 0.01145 -0.0023 1.0000 0.0291
-7.750 -0.8004 0.01735 0.01095 0.0003 1.0000 0.0300
-7.500 -0.7753 0.01686 0.01040 0.0006 0.9990 0.0310
-7.250 -0.7427 0.01587 0.00937 -0.0008 0.9963 0.0327
-7.000 -0.7086 0.01529 0.00881 -0.0024 0.9925 0.0347
-6.750 -0.6752 0.01478 0.00825 -0.0038 0.9864 0.0368
-6.500 -0.6433 0.01410 0.00753 -0.0048 0.9801 0.0390
-6.250 -0.6102 0.01350 0.00696 -0.0061 0.9746 0.0423
-6.000 -0.5741 0.01311 0.00652 -0.0078 0.9699 0.0457
-5.750 -0.5374 0.01242 0.00588 -0.0099 0.9662 0.0516
-5.500 -0.4994 0.01192 0.00540 -0.0122 0.9607 0.0589
-5.250 -0.4556 0.01145 0.00497 -0.0158 0.9567 0.0697
-5.000 -0.4134 0.01105 0.00463 -0.0191 0.9500 0.0829
-4.750 -0.3705 0.01072 0.00432 -0.0225 0.9418 0.0966
-4.500 -0.3362 0.01049 0.00410 -0.0239 0.9290 0.1089
-4.250 -0.3064 0.01032 0.00392 -0.0243 0.9144 0.1204
-4.000 -0.2798 0.01012 0.00372 -0.0239 0.8988 0.1331
-3.750 -0.2545 0.00990 0.00351 -0.0233 0.8820 0.1471
-3.500 -0.2297 0.00967 0.00330 -0.0225 0.8639 0.1646
-3.250 -0.2068 0.00936 0.00305 -0.0214 0.8435 0.1937
-3.000 -0.1911 0.00853 0.00272 -0.0191 0.8210 0.3291
-2.750 -0.1736 0.00802 0.00254 -0.0169 0.7981 0.4404
-2.500 -0.1543 0.00771 0.00241 -0.0150 0.7741 0.5117
-2.250 -0.1343 0.00751 0.00231 -0.0131 0.7506 0.5700
-2.000 -0.1136 0.00735 0.00223 -0.0114 0.7277 0.6183
-1.750 -0.0931 0.00723 0.00219 -0.0095 0.7060 0.6661
-1.500 -0.0715 0.00716 0.00217 -0.0079 0.6859 0.7063
-1.250 -0.0488 0.00715 0.00216 -0.0065 0.6674 0.7402
-1.000 -0.0255 0.00715 0.00216 -0.0053 0.6497 0.7704
-0.750 -0.0013 0.00717 0.00216 -0.0042 0.6334 0.7951
-0.500 0.0234 0.00720 0.00218 -0.0033 0.6180 0.8170
-0.250 0.0489 0.00724 0.00220 -0.0025 0.6030 0.8371
0.000 0.0753 0.00728 0.00222 -0.0020 0.5887 0.8544
0.250 0.1022 0.00733 0.00225 -0.0015 0.5750 0.8720
0.500 0.1300 0.00739 0.00229 -0.0013 0.5614 0.8887
0.750 0.1591 0.00747 0.00233 -0.0014 0.5481 0.9050
1.000 0.1904 0.00756 0.00238 -0.0019 0.5346 0.9214
1.500 0.2595 0.00776 0.00246 -0.0047 0.5066 0.9435
1.750 0.3014 0.00790 0.00254 -0.0079 0.4914 0.9483
2.000 0.3384 0.00803 0.00261 -0.0099 0.4771 0.9551
2.250 0.3804 0.00820 0.00270 -0.0131 0.4624 0.9580
2.500 0.4205 0.00838 0.00282 -0.0158 0.4480 0.9610
2.750 0.4577 0.00857 0.00295 -0.0178 0.4344 0.9650
3.000 0.4938 0.00878 0.00309 -0.0196 0.4214 0.9693
3.250 0.5319 0.00901 0.00325 -0.0219 0.4078 0.9723
3.500 0.5683 0.00920 0.00340 -0.0238 0.3950 0.9766
3.750 0.6045 0.00939 0.00355 -0.0257 0.3829 0.9804
4.000 0.6403 0.00959 0.00370 -0.0276 0.3708 0.9844
4.250 0.6749 0.00980 0.00386 -0.0292 0.3585 0.9889
4.500 0.7106 0.01000 0.00402 -0.0311 0.3466 0.9929
4.750 0.7469 0.01017 0.00417 -0.0331 0.3352 0.9960
5.000 0.7842 0.01034 0.00430 -0.0353 0.3235 0.9985
5.250 0.8171 0.01052 0.00444 -0.0367 0.3115 1.0000
5.500 0.8378 0.01062 0.00453 -0.0355 0.3012 1.0000
5.750 0.8583 0.01075 0.00464 -0.0342 0.2916 1.0000
6.000 0.8781 0.01093 0.00479 -0.0327 0.2817 1.0000
6.250 0.8986 0.01107 0.00493 -0.0314 0.2718 1.0000
6.500 0.9188 0.01127 0.00511 -0.0300 0.2620 1.0000
7.000 0.9601 0.01174 0.00552 -0.0274 0.2401 1.0000
7.250 0.9811 0.01200 0.00574 -0.0262 0.2274 1.0000
7.500 1.0021 0.01229 0.00599 -0.0250 0.2150 1.0000
7.750 1.0230 0.01262 0.00627 -0.0238 0.2038 1.0000
8.000 1.0439 0.01296 0.00657 -0.0226 0.1930 1.0000
8.250 1.0657 0.01325 0.00687 -0.0216 0.1841 1.0000
8.500 1.0863 0.01363 0.00722 -0.0204 0.1759 1.0000
8.750 1.1080 0.01394 0.00754 -0.0194 0.1676 1.0000
9.000 1.1288 0.01431 0.00790 -0.0182 0.1592 1.0000
9.250 1.1494 0.01469 0.00827 -0.0171 0.1510 1.0000
9.500 1.1705 0.01505 0.00864 -0.0160 0.1436 1.0000
9.750 1.1896 0.01552 0.00908 -0.0147 0.1344 1.0000
10.000 1.2102 0.01589 0.00946 -0.0136 0.1248 1.0000
10.250 1.2279 0.01645 0.00995 -0.0121 0.1098 1.0000
10.500 1.2361 0.01763 0.01083 -0.0092 0.0687 1.0000
10.750 1.2306 0.01961 0.01249 -0.0044 0.0304 1.0000
11.000 1.2385 0.02066 0.01357 -0.0014 0.0257 1.0000
11.250 1.2462 0.02145 0.01444 0.0017 0.0237 1.0000
11.500 1.2509 0.02233 0.01537 0.0052 0.0223 1.0000
11.750 1.2528 0.02345 0.01657 0.0087 0.0211 1.0000
12.000 1.2545 0.02474 0.01795 0.0117 0.0202 1.0000
12.250 1.2602 0.02592 0.01922 0.0139 0.0196 1.0000
12.500 1.2644 0.02732 0.02071 0.0159 0.0190 1.0000
12.750 1.2668 0.02899 0.02247 0.0177 0.0184 1.0000
13.000 1.2681 0.03092 0.02450 0.0191 0.0180 1.0000
13.250 1.2670 0.03325 0.02694 0.0201 0.0176 1.0000
13.500 1.2632 0.03609 0.02988 0.0206 0.0172 1.0000
13.750 1.2563 0.03953 0.03343 0.0205 0.0169 1.0000
14.000 1.2451 0.04371 0.03773 0.0200 0.0166 1.0000
14.250 1.2325 0.04824 0.04237 0.0191 0.0164 1.0000
14.500 1.2297 0.05172 0.04596 0.0183 0.0163 1.0000
14.750 1.2248 0.05551 0.04986 0.0174 0.0161 1.0000
15.000 1.2182 0.05955 0.05401 0.0163 0.0159 1.0000
15.250 1.2110 0.06373 0.05830 0.0151 0.0157 1.0000
15.500 1.2034 0.06808 0.06275 0.0138 0.0155 1.0000
15.750 1.1950 0.07256 0.06733 0.0125 0.0154 1.0000
16.000 1.1875 0.07704 0.07190 0.0110 0.0152 1.0000
16.250 1.1802 0.08155 0.07650 0.0095 0.0150 1.0000
16.500 1.1733 0.08601 0.08104 0.0081 0.0148 1.0000
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