FX 60-157 AIRFOIL (fx60157-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 60-157 AIRFOIL (fx60157-il) Reynolds number: 500,000 Max Cl/Cd: 69.99 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx60157-il-500000-n5.txt Download as CSV file: xf-fx60157-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-157 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
------ -------- --------- --------- -------- -------- --------
-16.500 -0.7318 0.09697 0.09384 -0.0648 1.0000 0.0056
-16.250 -0.7580 0.08625 0.08293 -0.0716 0.9995 0.0055
-16.000 -0.7830 0.07630 0.07276 -0.0785 0.9987 0.0055
-15.750 -0.7940 0.06934 0.06564 -0.0837 0.9978 0.0055
-15.500 -0.8026 0.06313 0.05925 -0.0885 0.9965 0.0055
-15.250 -0.8087 0.05764 0.05360 -0.0928 0.9950 0.0055
-15.000 -0.8149 0.05242 0.04818 -0.0967 0.9935 0.0056
-14.750 -0.8104 0.04941 0.04505 -0.0986 0.9916 0.0055
-14.500 -0.8159 0.04522 0.04069 -0.1009 0.9892 0.0056
-14.250 -0.8141 0.04198 0.03729 -0.1028 0.9869 0.0057
-14.000 -0.8086 0.03914 0.03433 -0.1047 0.9849 0.0058
-13.750 -0.7980 0.03687 0.03193 -0.1064 0.9833 0.0059
-13.500 -0.7884 0.03478 0.02971 -0.1075 0.9813 0.0060
-13.250 -0.7817 0.03306 0.02789 -0.1073 0.9773 0.0060
-13.000 -0.7682 0.03153 0.02627 -0.1079 0.9746 0.0063
-12.750 -0.7530 0.02993 0.02456 -0.1089 0.9724 0.0064
-12.500 -0.7350 0.02849 0.02301 -0.1101 0.9708 0.0065
-12.250 -0.7148 0.02720 0.02163 -0.1113 0.9696 0.0067
-12.000 -0.7062 0.02612 0.02046 -0.1099 0.9644 0.0069
-11.750 -0.6890 0.02505 0.01930 -0.1101 0.9615 0.0070
-11.500 -0.6691 0.02397 0.01814 -0.1107 0.9594 0.0071
-11.250 -0.6468 0.02297 0.01704 -0.1116 0.9577 0.0072
-11.000 -0.6227 0.02199 0.01597 -0.1128 0.9563 0.0074
-10.750 -0.6031 0.02112 0.01505 -0.1129 0.9534 0.0077
-10.500 -0.5883 0.02040 0.01429 -0.1119 0.9485 0.0081
-10.250 -0.5647 0.01966 0.01352 -0.1125 0.9459 0.0085
-10.000 -0.5382 0.01896 0.01277 -0.1136 0.9440 0.0089
-9.750 -0.5097 0.01830 0.01207 -0.1150 0.9424 0.0093
-9.500 -0.4796 0.01772 0.01149 -0.1166 0.9410 0.0106
-9.250 -0.4666 0.01729 0.01103 -0.1148 0.9356 0.0115
-9.000 -0.4471 0.01683 0.01053 -0.1141 0.9316 0.0129
-8.750 -0.4228 0.01639 0.01002 -0.1143 0.9289 0.0148
-8.500 -0.3965 0.01588 0.00946 -0.1150 0.9266 0.0161
-8.250 -0.3698 0.01541 0.00895 -0.1158 0.9243 0.0174
-8.000 -0.3589 0.01512 0.00862 -0.1132 0.9182 0.0184
-7.750 -0.3367 0.01464 0.00810 -0.1130 0.9145 0.0198
-7.500 -0.3099 0.01419 0.00762 -0.1137 0.9118 0.0210
-7.250 -0.2800 0.01379 0.00716 -0.1148 0.9097 0.0223
-7.000 -0.2633 0.01352 0.00687 -0.1131 0.9050 0.0230
-6.750 -0.2419 0.01322 0.00655 -0.1124 0.9011 0.0239
-6.500 -0.2161 0.01291 0.00622 -0.1125 0.8980 0.0250
-6.250 -0.1875 0.01261 0.00591 -0.1131 0.8956 0.0267
-6.000 -0.1574 0.01231 0.00561 -0.1141 0.8936 0.0303
-5.750 -0.1376 0.01211 0.00542 -0.1129 0.8895 0.0339
-5.500 -0.1142 0.01191 0.00520 -0.1123 0.8854 0.0383
-5.250 -0.0878 0.01161 0.00491 -0.1125 0.8819 0.0438
-5.000 -0.0580 0.01132 0.00464 -0.1133 0.8790 0.0512
-4.750 -0.0310 0.01108 0.00441 -0.1135 0.8752 0.0636
-4.500 -0.0083 0.01086 0.00421 -0.1128 0.8699 0.0735
-4.250 0.0190 0.01055 0.00398 -0.1131 0.8657 0.0971
-4.000 0.0498 0.01016 0.00370 -0.1143 0.8624 0.1309
-3.750 0.0744 0.00973 0.00346 -0.1143 0.8572 0.1883
-3.500 0.1009 0.00917 0.00318 -0.1148 0.8514 0.2658
-3.250 0.1331 0.00862 0.00290 -0.1165 0.8472 0.3499
-3.000 0.1629 0.00834 0.00273 -0.1174 0.8430 0.3894
-2.750 0.1926 0.00790 0.00255 -0.1184 0.8373 0.4622
-2.500 0.2258 0.00751 0.00242 -0.1201 0.8324 0.5417
-2.250 0.2566 0.00738 0.00246 -0.1209 0.8270 0.5974
-2.000 0.2846 0.00738 0.00252 -0.1209 0.8199 0.6262
-1.750 0.3149 0.00741 0.00252 -0.1214 0.8128 0.6418
-1.500 0.3418 0.00744 0.00254 -0.1212 0.8037 0.6501
-1.250 0.3713 0.00748 0.00252 -0.1215 0.7958 0.6584
-1.000 0.3989 0.00752 0.00255 -0.1215 0.7876 0.6643
-0.750 0.4273 0.00758 0.00257 -0.1216 0.7787 0.6701
-0.500 0.4557 0.00764 0.00256 -0.1217 0.7680 0.6771
-0.250 0.4819 0.00772 0.00264 -0.1213 0.7561 0.6816
0.000 0.5085 0.00781 0.00268 -0.1210 0.7415 0.6860
0.250 0.5341 0.00790 0.00267 -0.1206 0.7212 0.6890
0.500 0.5576 0.00805 0.00267 -0.1197 0.6918 0.6917
0.750 0.5788 0.00827 0.00270 -0.1183 0.6578 0.6943
1.000 0.5960 0.00858 0.00283 -0.1161 0.6155 0.6967
1.250 0.6151 0.00888 0.00297 -0.1144 0.5830 0.6993
1.500 0.6350 0.00916 0.00311 -0.1128 0.5530 0.7019
1.750 0.6563 0.00941 0.00325 -0.1117 0.5285 0.7045
2.000 0.6765 0.00970 0.00340 -0.1103 0.4994 0.7071
2.250 0.6961 0.00999 0.00355 -0.1088 0.4725 0.7095
2.500 0.7161 0.01026 0.00371 -0.1074 0.4466 0.7113
2.750 0.7351 0.01056 0.00390 -0.1058 0.4203 0.7131
3.000 0.7546 0.01087 0.00412 -0.1043 0.3937 0.7149
3.250 0.7732 0.01126 0.00435 -0.1027 0.3606 0.7168
3.500 0.7917 0.01170 0.00462 -0.1012 0.3269 0.7187
3.750 0.8103 0.01218 0.00492 -0.0997 0.2917 0.7208
4.000 0.8301 0.01261 0.00520 -0.0985 0.2613 0.7227
4.250 0.8497 0.01307 0.00550 -0.0973 0.2324 0.7244
4.500 0.8719 0.01340 0.00575 -0.0966 0.2162 0.7260
4.750 0.8929 0.01378 0.00604 -0.0956 0.1949 0.7274
5.000 0.9138 0.01414 0.00634 -0.0946 0.1814 0.7288
5.250 0.9353 0.01446 0.00663 -0.0937 0.1699 0.7301
5.500 0.9566 0.01481 0.00695 -0.0928 0.1573 0.7316
5.750 0.9770 0.01521 0.00729 -0.0918 0.1415 0.7332
6.000 0.9969 0.01565 0.00767 -0.0907 0.1277 0.7350
6.250 1.0171 0.01607 0.00805 -0.0897 0.1167 0.7370
6.500 1.0363 0.01657 0.00847 -0.0885 0.0996 0.7391
6.750 1.0551 0.01710 0.00893 -0.0873 0.0867 0.7413
7.000 1.0748 0.01757 0.00937 -0.0863 0.0779 0.7432
7.250 1.0925 0.01812 0.00989 -0.0850 0.0627 0.7450
7.500 1.1107 0.01865 0.01039 -0.0837 0.0556 0.7466
7.750 1.1292 0.01917 0.01092 -0.0825 0.0505 0.7482
8.000 1.1491 0.01959 0.01138 -0.0816 0.0475 0.7499
8.250 1.1655 0.02027 0.01203 -0.0802 0.0342 0.7518
8.500 1.1830 0.02088 0.01263 -0.0790 0.0313 0.7535
8.750 1.2009 0.02145 0.01323 -0.0779 0.0290 0.7552
9.000 1.2195 0.02200 0.01382 -0.0768 0.0274 0.7568
9.250 1.2366 0.02266 0.01451 -0.0757 0.0249 0.7583
9.500 1.2541 0.02326 0.01517 -0.0746 0.0234 0.7598
9.750 1.2713 0.02388 0.01584 -0.0734 0.0204 0.7612
10.000 1.2863 0.02466 0.01667 -0.0721 0.0178 0.7627
10.250 1.3011 0.02546 0.01750 -0.0707 0.0163 0.7642
10.500 1.3158 0.02629 0.01837 -0.0694 0.0157 0.7658
10.750 1.3299 0.02717 0.01930 -0.0681 0.0151 0.7677
11.000 1.3435 0.02812 0.02030 -0.0668 0.0145 0.7697
11.250 1.3567 0.02910 0.02134 -0.0655 0.0142 0.7716
11.500 1.3697 0.03012 0.02242 -0.0643 0.0138 0.7734
11.750 1.3819 0.03121 0.02358 -0.0630 0.0136 0.7751
12.000 1.3938 0.03234 0.02479 -0.0618 0.0133 0.7766
12.250 1.4049 0.03353 0.02608 -0.0605 0.0131 0.7782
12.500 1.4152 0.03482 0.02747 -0.0593 0.0127 0.7799
12.750 1.4245 0.03622 0.02896 -0.0581 0.0124 0.7816
13.000 1.4330 0.03774 0.03058 -0.0569 0.0122 0.7835
13.250 1.4405 0.03939 0.03232 -0.0558 0.0119 0.7854
13.500 1.4472 0.04117 0.03419 -0.0547 0.0117 0.7873
13.750 1.4528 0.04311 0.03623 -0.0537 0.0115 0.7892
14.000 1.4570 0.04525 0.03847 -0.0528 0.0113 0.7910
14.250 1.4600 0.04759 0.04092 -0.0520 0.0112 0.7927
14.500 1.4617 0.05015 0.04359 -0.0514 0.0110 0.7946
14.750 1.4614 0.05302 0.04658 -0.0509 0.0108 0.7966
15.000 1.4653 0.05552 0.04920 -0.0506 0.0107 0.7988
15.250 1.4684 0.05823 0.05202 -0.0506 0.0106 0.8010
15.500 1.4705 0.06114 0.05505 -0.0507 0.0105 0.8031
15.750 1.4716 0.06429 0.05833 -0.0510 0.0104 0.8051
16.000 1.4716 0.06770 0.06186 -0.0515 0.0102 0.8070
16.250 1.4704 0.07138 0.06567 -0.0523 0.0101 0.8088
16.500 1.4683 0.07532 0.06974 -0.0532 0.0100 0.8106
16.750 1.4649 0.07957 0.07413 -0.0545 0.0098 0.8125
17.000 1.4604 0.08410 0.07880 -0.0560 0.0097 0.8145
17.250 1.4550 0.08892 0.08376 -0.0577 0.0095 0.8166
17.500 1.4487 0.09401 0.08898 -0.0598 0.0094 0.8187
17.750 1.4417 0.09934 0.09445 -0.0621 0.0092 0.8207
18.000 1.4331 0.10503 0.10028 -0.0647 0.0090 0.8225
18.500 1.4134 0.11717 0.11268 -0.0707 0.0087 0.8259
18.750 1.4025 0.12354 0.11919 -0.0741 0.0086 0.8277
19.000 1.3910 0.13011 0.12590 -0.0777 0.0085 0.8295
|
Polar data table (+)
Polar graphs
<< Back to FX 60-157 AIRFOIL (fx60157-il)