FX 74-130 WP1 (fx74130wp1-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 74-130 WP1 (fx74130wp1-il) Reynolds number: 200,000 Max Cl/Cd: 71.21 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74130wp1-il-200000-n5.txt Download as CSV file: xf-fx74130wp1-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 74-130 WP1
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1309 0.09252 0.08811 -0.1189 0.8656 0.0260
-10.250 -0.1289 0.08895 0.08455 -0.1212 0.8634 0.0262
-9.250 -0.1257 0.07256 0.06819 -0.1263 0.8554 0.0181
-9.000 -0.1269 0.06904 0.06471 -0.1279 0.8528 0.0174
-8.750 -0.1322 0.06476 0.06045 -0.1309 0.8500 0.0167
-8.500 -0.1432 0.06030 0.05596 -0.1333 0.8472 0.0161
-8.250 -0.1590 0.05672 0.05231 -0.1332 0.8443 0.0156
-7.750 -0.1840 0.04615 0.04129 -0.1310 0.8379 0.0134
-7.500 -0.1840 0.04292 0.03786 -0.1296 0.8354 0.0134
-7.250 -0.1797 0.03988 0.03456 -0.1282 0.8333 0.0133
-7.000 -0.1728 0.03656 0.03087 -0.1266 0.8316 0.0134
-6.750 -0.1645 0.03362 0.02753 -0.1249 0.8296 0.0137
-6.500 -0.1523 0.03189 0.02567 -0.1239 0.8271 0.0144
-6.250 -0.1346 0.03095 0.02462 -0.1233 0.8248 0.0154
-6.000 -0.1175 0.02885 0.02220 -0.1221 0.8227 0.0157
-5.750 -0.0984 0.02649 0.01942 -0.1210 0.8209 0.0155
-5.500 -0.0766 0.02448 0.01702 -0.1201 0.8195 0.0155
-5.250 -0.0528 0.02288 0.01510 -0.1195 0.8182 0.0156
-5.000 -0.0278 0.02156 0.01351 -0.1191 0.8170 0.0158
-4.750 -0.0056 0.02058 0.01239 -0.1181 0.8148 0.0163
-4.500 0.0164 0.01975 0.01144 -0.1172 0.8123 0.0170
-4.250 0.0392 0.01900 0.01061 -0.1164 0.8101 0.0177
-4.000 0.0627 0.01841 0.00993 -0.1158 0.8083 0.0188
-3.750 0.0860 0.01779 0.00930 -0.1154 0.8067 0.0212
-3.500 0.1109 0.01737 0.00885 -0.1152 0.8052 0.0238
-3.250 0.1365 0.01692 0.00830 -0.1149 0.8039 0.0261
-3.000 0.1624 0.01644 0.00777 -0.1149 0.8027 0.0310
-2.750 0.1821 0.01628 0.00762 -0.1138 0.7994 0.0408
-2.500 0.2042 0.01598 0.00743 -0.1131 0.7968 0.0722
-2.250 0.2253 0.01510 0.00728 -0.1130 0.7946 0.2555
-2.000 0.2329 0.01387 0.00785 -0.1090 0.7925 0.6874
-1.750 0.2552 0.01433 0.00831 -0.1072 0.7910 0.7825
-1.500 0.2768 0.01476 0.00865 -0.1051 0.7896 0.8175
-1.250 0.2888 0.01522 0.00912 -0.1007 0.7874 0.8431
-1.000 0.2965 0.01567 0.00959 -0.0963 0.7830 0.8613
-0.750 0.3128 0.01583 0.00971 -0.0937 0.7804 0.8705
-0.500 0.3388 0.01588 0.00965 -0.0936 0.7785 0.8767
-0.250 0.3639 0.01585 0.00956 -0.0930 0.7769 0.8798
0.000 0.3915 0.01583 0.00946 -0.0932 0.7756 0.8824
0.250 0.4204 0.01582 0.00938 -0.0936 0.7746 0.8848
0.500 0.4322 0.01624 0.00983 -0.0914 0.7690 0.8885
0.750 0.4575 0.01636 0.00991 -0.0914 0.7662 0.8906
1.000 0.4834 0.01639 0.00991 -0.0914 0.7643 0.8921
1.250 0.5116 0.01638 0.00987 -0.0917 0.7627 0.8935
1.500 0.5413 0.01634 0.00981 -0.0923 0.7615 0.8948
1.750 0.5721 0.01629 0.00974 -0.0931 0.7604 0.8961
2.250 0.6061 0.01684 0.01037 -0.0902 0.7504 0.9005
2.500 0.6373 0.01676 0.01030 -0.0912 0.7487 0.9014
2.750 0.6698 0.01666 0.01020 -0.0923 0.7474 0.9022
3.250 0.7054 0.01721 0.01087 -0.0897 0.7374 0.9058
3.500 0.7361 0.01707 0.01078 -0.0904 0.7355 0.9065
3.750 0.7695 0.01686 0.01060 -0.0916 0.7339 0.9071
4.250 0.8058 0.01710 0.01102 -0.0887 0.7227 0.9109
4.500 0.8417 0.01668 0.01066 -0.0901 0.7204 0.9115
4.750 0.8495 0.01701 0.01107 -0.0869 0.7118 0.9139
5.000 0.8841 0.01652 0.01066 -0.0880 0.7078 0.9145
5.250 0.8957 0.01662 0.01087 -0.0853 0.6987 0.9167
5.500 0.9341 0.01587 0.01020 -0.0869 0.6926 0.9172
5.750 0.9470 0.01589 0.01031 -0.0842 0.6804 0.9195
6.000 0.9686 0.01563 0.01012 -0.0830 0.6668 0.9216
6.250 0.9917 0.01531 0.00986 -0.0819 0.6464 0.9235
6.500 1.0193 0.01487 0.00938 -0.0814 0.6114 0.9249
6.750 1.0440 0.01466 0.00871 -0.0802 0.5259 0.9262
7.000 1.0372 0.01583 0.00938 -0.0747 0.4480 0.9303
7.250 1.0300 0.01721 0.01043 -0.0697 0.3874 0.9348
7.500 1.0231 0.01875 0.01168 -0.0651 0.3278 0.9402
8.000 1.0220 0.02176 0.01418 -0.0588 0.2200 0.9554
8.250 1.0263 0.02326 0.01542 -0.0567 0.1684 0.9711
8.500 1.0316 0.02471 0.01662 -0.0547 0.1227 1.0000
8.750 1.0401 0.02616 0.01787 -0.0532 0.0874 1.0000
9.000 1.0514 0.02744 0.01906 -0.0521 0.0651 1.0000
9.250 1.0630 0.02874 0.02029 -0.0509 0.0509 1.0000
9.500 1.0759 0.02995 0.02155 -0.0499 0.0426 1.0000
9.750 1.0881 0.03123 0.02286 -0.0488 0.0371 1.0000
10.000 1.1013 0.03245 0.02417 -0.0479 0.0335 1.0000
10.250 1.1122 0.03386 0.02563 -0.0468 0.0304 1.0000
10.500 1.1222 0.03536 0.02722 -0.0456 0.0281 1.0000
10.750 1.1350 0.03666 0.02863 -0.0447 0.0258 1.0000
11.000 1.1462 0.03811 0.03018 -0.0438 0.0240 1.0000
11.250 1.1561 0.03971 0.03187 -0.0427 0.0225 1.0000
11.500 1.1621 0.04173 0.03393 -0.0414 0.0208 1.0000
11.750 1.1755 0.04308 0.03544 -0.0407 0.0192 1.0000
12.000 1.1864 0.04473 0.03721 -0.0399 0.0181 1.0000
12.250 1.1970 0.04638 0.03896 -0.0391 0.0167 1.0000
12.500 1.2063 0.04816 0.04080 -0.0384 0.0155 1.0000
12.750 1.2139 0.05030 0.04303 -0.0375 0.0144 1.0000
13.000 1.2249 0.05209 0.04502 -0.0368 0.0135 1.0000
13.250 1.2347 0.05411 0.04723 -0.0360 0.0127 1.0000
13.500 1.2431 0.05626 0.04955 -0.0353 0.0121 1.0000
13.750 1.2503 0.05854 0.05198 -0.0347 0.0114 1.0000
14.000 1.2561 0.06098 0.05456 -0.0342 0.0110 1.0000
14.250 1.2600 0.06363 0.05733 -0.0338 0.0106 1.0000
14.500 1.2611 0.06690 0.06074 -0.0332 0.0101 1.0000
14.750 1.2625 0.07007 0.06419 -0.0329 0.0098 1.0000
15.000 1.2616 0.07359 0.06799 -0.0327 0.0093 1.0000
15.250 1.2583 0.07750 0.07216 -0.0328 0.0090 1.0000
15.500 1.2530 0.08172 0.07663 -0.0331 0.0086 1.0000
15.750 1.2458 0.08635 0.08151 -0.0339 0.0084 1.0000
16.000 1.2365 0.09146 0.08686 -0.0350 0.0082 1.0000
16.250 1.2250 0.09714 0.09278 -0.0366 0.0081 1.0000
16.500 1.2117 0.10335 0.09923 -0.0389 0.0080 1.0000
16.750 1.1966 0.11019 0.10631 -0.0418 0.0080 1.0000
17.000 1.1801 0.11771 0.11407 -0.0456 0.0079 1.0000
17.250 1.1610 0.12628 0.12287 -0.0504 0.0080 1.0000
17.500 1.1388 0.13626 0.13308 -0.0565 0.0080 1.0000
17.750 1.1125 0.14828 0.14533 -0.0643 0.0082 1.0000
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