FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 60-160 AIRFOIL (fx60160-il) Reynolds number: 500,000 Max Cl/Cd: 88.96 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60160-il-500000-n5.txt Download as CSV file: xf-fx60160-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-160 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7825 0.07449 0.07153 -0.0826 1.0000 0.0153
-16.000 -0.8198 0.06522 0.06204 -0.0878 1.0000 0.0153
-15.750 -0.8372 0.05988 0.05657 -0.0902 1.0000 0.0154
-15.500 -0.8532 0.05530 0.05186 -0.0918 1.0000 0.0156
-15.250 -0.8671 0.05150 0.04792 -0.0926 1.0000 0.0157
-15.000 -0.8796 0.04821 0.04452 -0.0927 1.0000 0.0159
-14.750 -0.8894 0.04551 0.04171 -0.0921 1.0000 0.0161
-14.500 -0.8949 0.04284 0.03891 -0.0922 0.9996 0.0163
-14.250 -0.8857 0.04009 0.03598 -0.0948 0.9978 0.0167
-14.000 -0.8758 0.03752 0.03322 -0.0971 0.9953 0.0171
-13.750 -0.8635 0.03547 0.03103 -0.0988 0.9925 0.0175
-13.500 -0.8493 0.03374 0.02925 -0.1006 0.9893 0.0179
-13.250 -0.8294 0.03247 0.02793 -0.1026 0.9865 0.0183
-13.000 -0.8092 0.03101 0.02639 -0.1048 0.9842 0.0186
-12.750 -0.7912 0.02988 0.02520 -0.1060 0.9803 0.0190
-12.500 -0.7720 0.02860 0.02382 -0.1074 0.9765 0.0195
-12.250 -0.7493 0.02732 0.02242 -0.1093 0.9737 0.0200
-12.000 -0.7268 0.02609 0.02106 -0.1110 0.9704 0.0206
-11.750 -0.7070 0.02497 0.01980 -0.1119 0.9650 0.0211
-11.500 -0.6801 0.02395 0.01863 -0.1139 0.9617 0.0215
-11.250 -0.6535 0.02265 0.01728 -0.1162 0.9585 0.0222
-11.000 -0.6368 0.02184 0.01640 -0.1160 0.9499 0.0226
-10.750 -0.6084 0.02123 0.01575 -0.1176 0.9451 0.0232
-10.500 -0.5901 0.02065 0.01509 -0.1170 0.9361 0.0237
-10.250 -0.5632 0.01999 0.01435 -0.1180 0.9297 0.0243
-10.000 -0.5442 0.01937 0.01365 -0.1172 0.9186 0.0249
-9.750 -0.5216 0.01876 0.01293 -0.1171 0.9076 0.0255
-9.500 -0.4978 0.01819 0.01225 -0.1171 0.8955 0.0261
-9.250 -0.4740 0.01762 0.01155 -0.1171 0.8818 0.0265
-9.000 -0.4526 0.01691 0.01072 -0.1166 0.8668 0.0270
-8.750 -0.4317 0.01631 0.01004 -0.1161 0.8518 0.0277
-8.500 -0.4098 0.01589 0.00952 -0.1155 0.8384 0.0283
-8.250 -0.3879 0.01553 0.00907 -0.1149 0.8267 0.0288
-8.000 -0.3654 0.01521 0.00868 -0.1144 0.8164 0.0296
-7.750 -0.3430 0.01488 0.00825 -0.1138 0.8072 0.0304
-7.500 -0.3204 0.01455 0.00784 -0.1132 0.7984 0.0312
-7.250 -0.2976 0.01420 0.00741 -0.1127 0.7911 0.0318
-7.000 -0.2743 0.01388 0.00701 -0.1122 0.7840 0.0325
-6.500 -0.2285 0.01312 0.00612 -0.1113 0.7710 0.0341
-6.250 -0.2044 0.01281 0.00578 -0.1109 0.7650 0.0353
-6.000 -0.1795 0.01259 0.00550 -0.1107 0.7599 0.0365
-5.750 -0.1542 0.01235 0.00524 -0.1105 0.7545 0.0378
-5.500 -0.1289 0.01213 0.00496 -0.1103 0.7491 0.0392
-5.250 -0.1033 0.01193 0.00469 -0.1101 0.7445 0.0403
-5.000 -0.0778 0.01167 0.00440 -0.1100 0.7398 0.0417
-4.750 -0.0523 0.01141 0.00412 -0.1098 0.7349 0.0439
-4.500 -0.0261 0.01124 0.00391 -0.1097 0.7303 0.0463
-4.250 0.0004 0.01109 0.00373 -0.1097 0.7261 0.0488
-4.000 0.0271 0.01094 0.00355 -0.1096 0.7216 0.0509
-3.750 0.0533 0.01074 0.00333 -0.1095 0.7170 0.0549
-3.250 0.1069 0.01046 0.00301 -0.1095 0.7086 0.0645
-3.000 0.1334 0.01028 0.00286 -0.1095 0.7040 0.0763
-2.750 0.1583 0.00987 0.00266 -0.1094 0.6995 0.1423
-2.500 0.1802 0.00897 0.00233 -0.1091 0.6953 0.3172
-2.250 0.2049 0.00850 0.00216 -0.1090 0.6904 0.4035
-2.000 0.2300 0.00819 0.00210 -0.1088 0.6856 0.4843
-1.750 0.2565 0.00810 0.00210 -0.1086 0.6813 0.5290
-1.500 0.2838 0.00806 0.00213 -0.1086 0.6768 0.5542
-1.250 0.3112 0.00807 0.00215 -0.1085 0.6720 0.5724
-1.000 0.3387 0.00810 0.00218 -0.1085 0.6676 0.5864
-0.750 0.3662 0.00815 0.00223 -0.1085 0.6633 0.6010
-0.500 0.3938 0.00819 0.00228 -0.1085 0.6585 0.6101
-0.250 0.4214 0.00825 0.00230 -0.1085 0.6536 0.6187
0.000 0.4487 0.00832 0.00236 -0.1084 0.6492 0.6262
0.250 0.4764 0.00836 0.00239 -0.1084 0.6441 0.6326
0.500 0.5037 0.00842 0.00244 -0.1083 0.6390 0.6371
0.750 0.5308 0.00849 0.00248 -0.1082 0.6342 0.6414
1.000 0.5583 0.00853 0.00253 -0.1082 0.6290 0.6459
1.250 0.5856 0.00860 0.00257 -0.1082 0.6235 0.6502
1.500 0.6123 0.00866 0.00263 -0.1080 0.6185 0.6531
1.750 0.6395 0.00871 0.00271 -0.1080 0.6130 0.6564
2.000 0.6661 0.00878 0.00277 -0.1078 0.6069 0.6603
2.250 0.6928 0.00886 0.00283 -0.1076 0.6013 0.6638
2.500 0.7194 0.00892 0.00291 -0.1075 0.5948 0.6667
2.750 0.7447 0.00900 0.00299 -0.1070 0.5865 0.6692
3.000 0.7698 0.00909 0.00307 -0.1065 0.5756 0.6717
3.250 0.7948 0.00919 0.00316 -0.1061 0.5654 0.6742
3.500 0.8188 0.00931 0.00325 -0.1054 0.5530 0.6769
3.750 0.8408 0.00948 0.00335 -0.1043 0.5334 0.6796
4.000 0.8607 0.00971 0.00347 -0.1028 0.5100 0.6820
4.250 0.8816 0.00991 0.00363 -0.1016 0.4900 0.6840
4.500 0.9012 0.01016 0.00382 -0.1001 0.4686 0.6863
4.750 0.9202 0.01044 0.00402 -0.0985 0.4485 0.6888
5.000 0.9393 0.01072 0.00424 -0.0969 0.4286 0.6913
5.250 0.9547 0.01106 0.00448 -0.0947 0.4046 0.6938
5.500 0.9661 0.01151 0.00477 -0.0917 0.3731 0.6962
5.750 0.9758 0.01204 0.00515 -0.0884 0.3363 0.6984
6.000 0.9824 0.01276 0.00565 -0.0847 0.2900 0.7007
6.250 0.9828 0.01378 0.00635 -0.0802 0.2255 0.7031
6.500 0.9788 0.01506 0.00726 -0.0751 0.1560 0.7056
6.750 0.9736 0.01646 0.00829 -0.0700 0.0847 0.7083
7.000 0.9874 0.01703 0.00883 -0.0680 0.0736 0.7109
7.250 1.0021 0.01757 0.00936 -0.0662 0.0658 0.7131
7.500 1.0171 0.01808 0.00991 -0.0645 0.0602 0.7154
7.750 1.0315 0.01864 0.01049 -0.0627 0.0554 0.7179
8.000 1.0468 0.01918 0.01106 -0.0611 0.0519 0.7204
8.250 1.0607 0.01980 0.01169 -0.0594 0.0486 0.7229
8.500 1.0740 0.02049 0.01239 -0.0576 0.0460 0.7256
8.750 1.0887 0.02111 0.01307 -0.0561 0.0447 0.7283
9.000 1.1026 0.02178 0.01380 -0.0546 0.0432 0.7307
9.250 1.1158 0.02251 0.01458 -0.0530 0.0417 0.7332
9.500 1.1285 0.02330 0.01541 -0.0515 0.0404 0.7360
9.750 1.1399 0.02420 0.01635 -0.0499 0.0384 0.7390
10.000 1.1498 0.02524 0.01742 -0.0482 0.0371 0.7422
10.250 1.1626 0.02610 0.01836 -0.0469 0.0365 0.7451
10.500 1.1750 0.02702 0.01935 -0.0456 0.0358 0.7480
10.750 1.1865 0.02802 0.02042 -0.0443 0.0353 0.7512
11.000 1.1985 0.02901 0.02148 -0.0431 0.0342 0.7548
11.250 1.2096 0.03010 0.02264 -0.0419 0.0334 0.7587
11.500 1.2201 0.03125 0.02386 -0.0408 0.0326 0.7626
11.750 1.2302 0.03247 0.02513 -0.0396 0.0315 0.7670
12.000 1.2388 0.03383 0.02655 -0.0385 0.0307 0.7716
12.250 1.2455 0.03540 0.02818 -0.0373 0.0296 0.7764
12.500 1.2558 0.03670 0.02958 -0.0364 0.0291 0.7822
12.750 1.2657 0.03806 0.03104 -0.0356 0.0287 0.7891
13.000 1.2761 0.03938 0.03248 -0.0348 0.0281 0.7977
13.250 1.2869 0.04068 0.03389 -0.0341 0.0268 0.8092
13.500 1.2970 0.04212 0.03545 -0.0335 0.0260 0.8270
13.750 1.3157 0.04373 0.03726 -0.0349 0.0245 0.8902
14.000 1.3314 0.04563 0.03926 -0.0363 0.0232 1.0000
14.250 1.3406 0.04731 0.04102 -0.0359 0.0224 1.0000
14.500 1.3502 0.04896 0.04273 -0.0355 0.0204 1.0000
14.750 1.3584 0.05078 0.04457 -0.0352 0.0184 1.0000
15.000 1.3654 0.05276 0.04661 -0.0348 0.0155 1.0000
15.500 1.3726 0.05754 0.05138 -0.0343 0.0107 1.0000
15.750 1.3736 0.06029 0.05418 -0.0340 0.0097 1.0000
16.000 1.3760 0.06297 0.05692 -0.0339 0.0092 1.0000
16.250 1.3783 0.06571 0.05975 -0.0339 0.0087 1.0000
16.500 1.3800 0.06856 0.06269 -0.0340 0.0084 1.0000
16.750 1.3803 0.07163 0.06584 -0.0342 0.0080 1.0000
17.000 1.3808 0.07474 0.06904 -0.0345 0.0077 1.0000
17.250 1.3804 0.07804 0.07242 -0.0349 0.0074 1.0000
17.500 1.3794 0.08147 0.07595 -0.0354 0.0071 1.0000
17.750 1.3795 0.08483 0.07940 -0.0361 0.0071 1.0000
18.000 1.3803 0.08811 0.08279 -0.0368 0.0069 1.0000
18.250 1.3796 0.09168 0.08647 -0.0377 0.0068 1.0000
18.500 1.3783 0.09538 0.09027 -0.0387 0.0066 1.0000
18.750 1.3768 0.09917 0.09417 -0.0398 0.0065 1.0000
19.000 1.3742 0.10317 0.09829 -0.0411 0.0063 1.0000
19.250 1.3713 0.10728 0.10251 -0.0426 0.0063 1.0000
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Polar data table (+)
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