FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-140 AIRFOIL (fx61140-il) Reynolds number: 500,000 Max Cl/Cd: 96.64 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61140-il-500000.txt Download as CSV file: xf-fx61140-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-140 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3294 0.08495 0.08295 -0.0420 1.0000 0.0171
-10.000 -0.3381 0.07927 0.07730 -0.0436 1.0000 0.0175
-9.750 -0.3503 0.07264 0.07070 -0.0458 1.0000 0.0175
-9.500 -0.3758 0.06201 0.06007 -0.0514 1.0000 0.0169
-9.250 -0.4088 0.05375 0.05174 -0.0552 1.0000 0.0166
-9.000 -0.4445 0.04778 0.04568 -0.0562 1.0000 0.0161
-8.750 -0.4757 0.04435 0.04220 -0.0544 1.0000 0.0160
-8.500 -0.4899 0.03979 0.03749 -0.0578 0.9959 0.0160
-8.250 -0.4844 0.03457 0.03205 -0.0642 0.9891 0.0163
-8.000 -0.4684 0.02983 0.02708 -0.0690 0.9850 0.0172
-7.750 -0.4545 0.02584 0.02282 -0.0713 0.9775 0.0183
-7.500 -0.4192 0.02532 0.02190 -0.0741 0.9736 0.0207
-7.250 -0.4140 0.01740 0.01340 -0.0765 0.9647 0.0216
-7.000 -0.4294 0.02437 0.01964 -0.0753 0.9709 0.0129
-6.750 -0.3999 0.02140 0.01634 -0.0763 0.9650 0.0125
-6.500 -0.3628 0.02022 0.01496 -0.0785 0.9615 0.0136
-6.250 -0.3339 0.01844 0.01301 -0.0788 0.9537 0.0137
-6.000 -0.3014 0.01658 0.01100 -0.0797 0.9484 0.0136
-5.750 -0.2722 0.01527 0.00960 -0.0800 0.9390 0.0138
-5.500 -0.2342 0.01423 0.00847 -0.0822 0.9322 0.0142
-5.250 -0.1949 0.01239 0.00655 -0.0855 0.9216 0.0161
-5.000 -0.1454 0.01157 0.00567 -0.0906 0.9101 0.0189
-4.750 -0.0889 0.01065 0.00465 -0.0973 0.8942 0.0256
-4.500 -0.0398 0.01001 0.00389 -0.1022 0.8686 0.0405
-4.250 0.0057 0.00791 0.00285 -0.1088 0.8382 0.3280
-4.000 0.0438 0.00705 0.00254 -0.1121 0.8080 0.5219
-3.750 0.0729 0.00708 0.00253 -0.1124 0.7802 0.5698
-3.500 0.1008 0.00723 0.00256 -0.1122 0.7556 0.5973
-3.250 0.1280 0.00744 0.00265 -0.1119 0.7330 0.6184
-3.000 0.1553 0.00774 0.00281 -0.1115 0.7124 0.6389
-2.750 0.1823 0.00805 0.00300 -0.1111 0.6938 0.6523
-2.500 0.2082 0.00825 0.00312 -0.1104 0.6770 0.6578
-2.250 0.2360 0.00842 0.00315 -0.1104 0.6613 0.6641
-2.000 0.2636 0.00855 0.00317 -0.1103 0.6469 0.6687
-1.750 0.2906 0.00870 0.00325 -0.1099 0.6336 0.6726
-1.500 0.3187 0.00882 0.00327 -0.1100 0.6210 0.6772
-1.250 0.3475 0.00892 0.00326 -0.1103 0.6095 0.6817
-1.000 0.3744 0.00904 0.00333 -0.1100 0.5990 0.6844
-0.750 0.4020 0.00916 0.00339 -0.1099 0.5888 0.6877
-0.500 0.4305 0.00926 0.00342 -0.1101 0.5792 0.6916
-0.250 0.4599 0.00936 0.00342 -0.1105 0.5703 0.6956
0.000 0.4871 0.00944 0.00349 -0.1103 0.5618 0.6979
0.250 0.5146 0.00955 0.00357 -0.1103 0.5540 0.7006
0.500 0.5425 0.00966 0.00364 -0.1103 0.5460 0.7038
0.750 0.5716 0.00975 0.00368 -0.1107 0.5383 0.7076
1.000 0.6002 0.00984 0.00372 -0.1109 0.5310 0.7106
1.250 0.6277 0.00992 0.00381 -0.1109 0.5239 0.7127
1.500 0.6551 0.01003 0.00390 -0.1108 0.5169 0.7151
1.750 0.6833 0.01012 0.00399 -0.1110 0.5101 0.7177
2.000 0.7119 0.01022 0.00406 -0.1112 0.5033 0.7208
2.250 0.7413 0.01034 0.00414 -0.1117 0.4970 0.7240
2.500 0.7686 0.01040 0.00422 -0.1117 0.4904 0.7259
2.750 0.7960 0.01053 0.00436 -0.1116 0.4844 0.7279
3.000 0.8238 0.01061 0.00448 -0.1117 0.4782 0.7303
3.250 0.8516 0.01076 0.00460 -0.1118 0.4723 0.7330
3.500 0.8803 0.01084 0.00473 -0.1121 0.4659 0.7358
3.750 0.9089 0.01097 0.00484 -0.1124 0.4596 0.7385
4.000 0.9360 0.01106 0.00498 -0.1123 0.4534 0.7404
4.250 0.9632 0.01116 0.00512 -0.1123 0.4465 0.7424
4.500 0.9904 0.01132 0.00531 -0.1123 0.4403 0.7447
4.750 1.0181 0.01142 0.00547 -0.1123 0.4335 0.7472
5.000 1.0458 0.01160 0.00563 -0.1125 0.4270 0.7497
5.250 1.0741 0.01170 0.00578 -0.1127 0.4186 0.7522
5.500 1.1004 0.01180 0.00594 -0.1126 0.4087 0.7542
5.750 1.1262 0.01191 0.00607 -0.1123 0.3945 0.7561
6.000 1.1522 0.01206 0.00624 -0.1120 0.3804 0.7581
6.250 1.1782 0.01224 0.00643 -0.1119 0.3662 0.7604
6.500 1.2041 0.01246 0.00664 -0.1117 0.3486 0.7630
6.750 1.2293 0.01278 0.00690 -0.1115 0.3259 0.7654
7.000 1.2533 0.01316 0.00720 -0.1110 0.2996 0.7674
7.250 1.2759 0.01361 0.00758 -0.1103 0.2708 0.7693
7.500 1.2964 0.01427 0.00808 -0.1094 0.2320 0.7714
7.750 1.3119 0.01542 0.00889 -0.1078 0.1705 0.7736
8.000 1.3240 0.01688 0.00995 -0.1058 0.1087 0.7759
8.250 1.3375 0.01815 0.01097 -0.1039 0.0667 0.7784
8.500 1.3519 0.01931 0.01196 -0.1022 0.0393 0.7807
8.750 1.3662 0.02027 0.01287 -0.1003 0.0243 0.7826
9.000 1.3765 0.02147 0.01403 -0.0978 0.0124 0.7845
9.250 1.3885 0.02242 0.01503 -0.0955 0.0091 0.7868
9.500 1.3968 0.02339 0.01611 -0.0926 0.0078 0.7893
9.750 1.4070 0.02431 0.01712 -0.0901 0.0071 0.7919
10.000 1.4158 0.02535 0.01825 -0.0876 0.0066 0.7942
10.250 1.4213 0.02656 0.01957 -0.0849 0.0061 0.7963
10.500 1.4223 0.02811 0.02125 -0.0819 0.0058 0.7984
10.750 1.4177 0.03020 0.02348 -0.0787 0.0055 0.8009
11.000 1.4125 0.03257 0.02601 -0.0761 0.0054 0.8036
11.250 1.4126 0.03478 0.02837 -0.0745 0.0053 0.8062
11.500 1.4114 0.03736 0.03108 -0.0734 0.0052 0.8086
11.750 1.4094 0.04019 0.03405 -0.0726 0.0051 0.8107
12.000 1.4062 0.04335 0.03735 -0.0721 0.0050 0.8128
12.250 1.4026 0.04677 0.04092 -0.0719 0.0050 0.8152
12.500 1.3990 0.05037 0.04466 -0.0720 0.0049 0.8177
12.750 1.3948 0.05419 0.04861 -0.0724 0.0049 0.8201
13.000 1.3911 0.05809 0.05263 -0.0728 0.0048 0.8223
13.250 1.3871 0.06205 0.05673 -0.0734 0.0048 0.8243
13.500 1.3832 0.06609 0.06092 -0.0740 0.0048 0.8261
13.750 1.3802 0.07012 0.06509 -0.0747 0.0048 0.8281
14.000 1.3768 0.07431 0.06941 -0.0755 0.0047 0.8301
14.250 1.3742 0.07853 0.07378 -0.0764 0.0047 0.8322
14.500 1.3718 0.08281 0.07821 -0.0774 0.0047 0.8343
14.750 1.3684 0.08736 0.08291 -0.0785 0.0047 0.8363
15.000 1.3655 0.09193 0.08764 -0.0799 0.0048 0.8383
15.250 1.3610 0.09685 0.09274 -0.0814 0.0048 0.8403
15.500 1.3555 0.10208 0.09815 -0.0831 0.0048 0.8423
15.750 1.3492 0.10758 0.10384 -0.0853 0.0048 0.8444
16.000 1.3423 0.11338 0.10984 -0.0879 0.0049 0.8467
16.250 1.3311 0.12014 0.11681 -0.0911 0.0049 0.8484
16.500 1.3210 0.12686 0.12371 -0.0946 0.0050 0.8505
16.750 1.3103 0.13386 0.13090 -0.0985 0.0050 0.8524
17.000 1.2983 0.14131 0.13854 -0.1029 0.0051 0.8545
17.250 1.2865 0.14894 0.14635 -0.1077 0.0051 0.8568
17.500 1.2723 0.15739 0.15499 -0.1132 0.0052 0.8591
17.750 1.2570 0.16647 0.16423 -0.1193 0.0053 0.8615
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