WORTMANN FX 71-120 AIRFOIL (fx71120-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 71-120 AIRFOIL (fx71120-il) Reynolds number: 200,000 Max Cl/Cd: 34.46 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx71120-il-200000.txt Download as CSV file: xf-fx71120-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 71-120 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.8602 0.06952 0.06480 -0.0396 1.0000 0.1107
-11.250 -0.8341 0.06694 0.06223 -0.0394 1.0000 0.1089
-11.000 -0.8449 0.06260 0.05784 -0.0391 1.0000 0.1078
-10.750 -0.8758 0.05798 0.05309 -0.0369 1.0000 0.1065
-10.500 -0.9184 0.05227 0.04708 -0.0329 1.0000 0.1042
-10.250 -0.9576 0.04588 0.04012 -0.0283 1.0000 0.1020
-10.000 -0.9594 0.04295 0.03691 -0.0256 1.0000 0.1020
-9.750 -0.9537 0.04069 0.03444 -0.0234 1.0000 0.1024
-9.500 -0.9492 0.03816 0.03162 -0.0208 1.0000 0.1023
-9.250 -0.9408 0.03594 0.02915 -0.0184 1.0000 0.1022
-9.000 -0.9278 0.03422 0.02725 -0.0165 1.0000 0.1025
-8.750 -0.9147 0.03242 0.02521 -0.0145 1.0000 0.1025
-8.500 -0.9006 0.03067 0.02323 -0.0125 1.0000 0.1023
-8.250 -0.8843 0.02918 0.02154 -0.0107 1.0000 0.1023
-8.000 -0.8666 0.02783 0.02002 -0.0090 1.0000 0.1023
-7.750 -0.8476 0.02670 0.01877 -0.0075 1.0000 0.1027
-7.500 -0.8279 0.02569 0.01767 -0.0061 1.0000 0.1033
-7.250 -0.8080 0.02470 0.01658 -0.0046 1.0000 0.1037
-7.000 -0.7877 0.02373 0.01551 -0.0032 1.0000 0.1039
-6.750 -0.7672 0.02283 0.01452 -0.0018 1.0000 0.1042
-6.500 -0.7464 0.02200 0.01363 -0.0004 1.0000 0.1046
-6.250 -0.7256 0.02123 0.01281 0.0010 1.0000 0.1051
-6.000 -0.7049 0.02052 0.01205 0.0024 1.0000 0.1056
-5.750 -0.6843 0.01987 0.01137 0.0039 1.0000 0.1062
-5.500 -0.6640 0.01927 0.01073 0.0054 1.0000 0.1069
-5.250 -0.6439 0.01871 0.01015 0.0069 1.0000 0.1076
-5.000 -0.6241 0.01820 0.00962 0.0085 1.0000 0.1084
-4.750 -0.6046 0.01774 0.00915 0.0102 1.0000 0.1092
-4.500 -0.5854 0.01733 0.00873 0.0118 1.0000 0.1102
-4.250 -0.5673 0.01666 0.00815 0.0136 1.0000 0.1118
-4.000 -0.5493 0.01623 0.00779 0.0153 1.0000 0.1137
-3.750 -0.5313 0.01591 0.00751 0.0171 1.0000 0.1155
-3.500 -0.5134 0.01561 0.00725 0.0188 1.0000 0.1177
-3.250 -0.4956 0.01535 0.00702 0.0205 1.0000 0.1202
-3.000 -0.4658 0.01501 0.00673 0.0199 0.9971 0.1243
-2.750 -0.4235 0.01463 0.00649 0.0168 0.9906 0.1327
-2.500 -0.3817 0.01417 0.00620 0.0139 0.9836 0.1507
-2.250 -0.3426 0.01325 0.00586 0.0113 0.9745 0.2256
-2.000 -0.3017 0.01244 0.00562 0.0084 0.9643 0.3323
-1.750 -0.2572 0.01177 0.00545 0.0052 0.9564 0.4312
-1.500 -0.2218 0.01123 0.00532 0.0040 0.9454 0.5159
-1.250 -0.1844 0.01077 0.00524 0.0026 0.9363 0.5926
-1.000 -0.1402 0.01030 0.00509 0.0002 0.9273 0.6631
-0.750 -0.1025 0.00992 0.00494 -0.0005 0.9115 0.7200
-0.500 -0.0658 0.00963 0.00483 -0.0009 0.8931 0.7653
-0.250 -0.0309 0.00946 0.00476 -0.0009 0.8709 0.8063
0.000 0.0000 0.00941 0.00476 0.0000 0.8415 0.8414
0.250 0.0309 0.00946 0.00476 0.0009 0.8061 0.8710
0.500 0.0659 0.00964 0.00483 0.0009 0.7652 0.8932
0.750 0.1023 0.00992 0.00494 0.0006 0.7199 0.9114
1.000 0.1408 0.01031 0.00510 -0.0003 0.6633 0.9274
1.250 0.1844 0.01077 0.00523 -0.0026 0.5926 0.9363
1.500 0.2216 0.01123 0.00532 -0.0039 0.5152 0.9454
1.750 0.2573 0.01177 0.00545 -0.0052 0.4318 0.9564
2.000 0.3017 0.01244 0.00562 -0.0084 0.3320 0.9643
2.250 0.3424 0.01326 0.00586 -0.0112 0.2238 0.9745
2.500 0.3815 0.01417 0.00621 -0.0138 0.1496 0.9836
2.750 0.4235 0.01463 0.00649 -0.0168 0.1323 0.9906
3.000 0.4659 0.01500 0.00672 -0.0199 0.1244 0.9971
3.250 0.4956 0.01535 0.00701 -0.0205 0.1203 1.0000
3.500 0.5133 0.01561 0.00725 -0.0188 0.1178 1.0000
3.750 0.5312 0.01590 0.00751 -0.0171 0.1156 1.0000
4.000 0.5493 0.01623 0.00779 -0.0153 0.1137 1.0000
4.250 0.5673 0.01665 0.00814 -0.0136 0.1120 1.0000
4.500 0.5854 0.01735 0.00874 -0.0118 0.1101 1.0000
4.750 0.6046 0.01774 0.00915 -0.0102 0.1092 1.0000
5.000 0.6241 0.01820 0.00962 -0.0085 0.1083 1.0000
5.250 0.6439 0.01871 0.01015 -0.0069 0.1076 1.0000
5.500 0.6640 0.01927 0.01073 -0.0054 0.1069 1.0000
5.750 0.6843 0.01987 0.01136 -0.0039 0.1062 1.0000
6.000 0.7049 0.02053 0.01205 -0.0024 0.1056 1.0000
6.250 0.7256 0.02123 0.01280 -0.0010 0.1051 1.0000
6.500 0.7464 0.02199 0.01363 0.0004 0.1046 1.0000
6.750 0.7672 0.02283 0.01453 0.0018 0.1043 1.0000
7.000 0.7877 0.02372 0.01550 0.0032 0.1039 1.0000
7.250 0.8080 0.02470 0.01658 0.0047 0.1037 1.0000
7.500 0.8279 0.02570 0.01768 0.0061 0.1033 1.0000
7.750 0.8476 0.02671 0.01878 0.0075 0.1027 1.0000
8.000 0.8666 0.02784 0.02003 0.0090 0.1024 1.0000
8.250 0.8844 0.02917 0.02153 0.0107 0.1023 1.0000
8.500 0.9007 0.03067 0.02323 0.0125 0.1023 1.0000
8.750 0.9149 0.03240 0.02518 0.0144 0.1025 1.0000
9.000 0.9280 0.03420 0.02722 0.0165 0.1025 1.0000
9.250 0.9407 0.03595 0.02915 0.0184 0.1022 1.0000
9.500 0.9492 0.03816 0.03163 0.0208 0.1022 1.0000
9.750 0.9539 0.04067 0.03442 0.0233 0.1024 1.0000
10.000 0.9595 0.04295 0.03691 0.0256 0.1020 1.0000
10.250 0.9532 0.04635 0.04065 0.0287 0.1023 1.0000
10.500 0.9194 0.05218 0.04698 0.0329 0.1041 1.0000
10.750 0.8759 0.05801 0.05312 0.0368 0.1065 1.0000
11.000 0.8473 0.06256 0.05779 0.0390 0.1079 1.0000
11.250 0.8378 0.06685 0.06213 0.0393 0.1089 1.0000
11.500 0.8649 0.06946 0.06473 0.0395 0.1107 1.0000
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Polar data table (+)
Polar graphs
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