FX S 03-182 AIRFOIL (fxs03182-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX S 03-182 AIRFOIL (fxs03182-il) Reynolds number: 500,000 Max Cl/Cd: 96.85 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxs03182-il-500000.txt Download as CSV file: xf-fxs03182-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX S 03-182 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3040 0.08702 0.08470 -0.1025 0.9472 0.0208
-12.500 -0.3185 0.07516 0.07263 -0.1162 0.9385 0.0209
-12.250 -0.3293 0.06564 0.06287 -0.1278 0.9251 0.0208
-12.000 -0.5012 0.03420 0.02949 -0.1329 0.8945 0.0081
-11.750 -0.4907 0.03276 0.02781 -0.1327 0.8739 0.0079
-11.500 -0.4811 0.03169 0.02655 -0.1318 0.8575 0.0078
-11.250 -0.4763 0.02906 0.02362 -0.1301 0.8449 0.0076
-11.000 -0.4660 0.02771 0.02207 -0.1289 0.8336 0.0075
-10.750 -0.4544 0.02619 0.02032 -0.1274 0.8240 0.0073
-10.500 -0.4423 0.02493 0.01889 -0.1259 0.8146 0.0072
-10.250 -0.4299 0.02389 0.01769 -0.1245 0.8063 0.0070
-10.000 -0.4185 0.02287 0.01653 -0.1229 0.7984 0.0070
-9.750 -0.4060 0.02203 0.01556 -0.1215 0.7910 0.0069
-9.500 -0.3942 0.02119 0.01461 -0.1201 0.7840 0.0069
-9.250 -0.3846 0.02025 0.01356 -0.1183 0.7776 0.0069
-9.000 -0.3724 0.01951 0.01274 -0.1169 0.7713 0.0069
-8.750 -0.3607 0.01877 0.01188 -0.1153 0.7660 0.0069
-8.500 -0.3487 0.01806 0.01111 -0.1138 0.7604 0.0070
-8.250 -0.3371 0.01736 0.01032 -0.1121 0.7554 0.0071
-8.000 -0.3257 0.01670 0.00957 -0.1103 0.7509 0.0072
-7.750 -0.3154 0.01612 0.00892 -0.1082 0.7461 0.0074
-7.500 -0.3065 0.01563 0.00833 -0.1058 0.7418 0.0076
-7.250 -0.2903 0.01523 0.00781 -0.1047 0.7381 0.0078
-7.000 -0.2726 0.01483 0.00738 -0.1036 0.7343 0.0081
-6.750 -0.2548 0.01438 0.00693 -0.1026 0.7304 0.0097
-6.500 -0.2344 0.01404 0.00660 -0.1019 0.7270 0.0107
-6.250 -0.2106 0.01385 0.00632 -0.1017 0.7239 0.0161
-6.000 -0.1879 0.01358 0.00603 -0.1013 0.7208 0.0193
-5.750 -0.1650 0.01328 0.00576 -0.1010 0.7178 0.0261
-5.500 -0.1412 0.01301 0.00551 -0.1008 0.7149 0.0312
-5.250 -0.1158 0.01283 0.00529 -0.1008 0.7124 0.0368
-5.000 -0.0898 0.01266 0.00507 -0.1010 0.7101 0.0430
-4.750 -0.0652 0.01237 0.00485 -0.1010 0.7077 0.0594
-4.500 -0.0438 0.01163 0.00446 -0.1010 0.7053 0.1374
-4.250 -0.0233 0.01038 0.00385 -0.1015 0.7028 0.2999
-4.000 0.0017 0.00918 0.00333 -0.1028 0.7006 0.4745
-3.750 0.0310 0.00913 0.00345 -0.1034 0.6985 0.5531
-3.500 0.0609 0.00925 0.00354 -0.1040 0.6965 0.5752
-3.250 0.0907 0.00939 0.00362 -0.1046 0.6945 0.5865
-3.000 0.1198 0.00951 0.00372 -0.1050 0.6925 0.5976
-2.750 0.1493 0.00968 0.00384 -0.1055 0.6906 0.6086
-2.500 0.1778 0.00986 0.00406 -0.1056 0.6887 0.6178
-2.250 0.2076 0.00998 0.00410 -0.1062 0.6869 0.6239
-2.000 0.2363 0.01006 0.00420 -0.1065 0.6852 0.6281
-1.750 0.2657 0.01021 0.00432 -0.1070 0.6836 0.6338
-1.500 0.2951 0.01037 0.00446 -0.1074 0.6821 0.6407
-1.250 0.3240 0.01063 0.00471 -0.1077 0.6804 0.6469
-1.000 0.3529 0.01073 0.00480 -0.1081 0.6788 0.6519
-0.750 0.3811 0.01076 0.00486 -0.1084 0.6771 0.6551
-0.500 0.4094 0.01084 0.00498 -0.1087 0.6755 0.6579
-0.250 0.4382 0.01092 0.00507 -0.1091 0.6739 0.6609
0.000 0.4676 0.01097 0.00510 -0.1097 0.6724 0.6632
0.250 0.4973 0.01099 0.00510 -0.1105 0.6708 0.6646
0.500 0.5273 0.01101 0.00509 -0.1113 0.6692 0.6660
0.750 0.5576 0.01107 0.00510 -0.1121 0.6678 0.6673
1.000 0.5871 0.01112 0.00515 -0.1128 0.6657 0.6687
1.250 0.6137 0.01106 0.00515 -0.1128 0.6623 0.6700
1.500 0.6416 0.01100 0.00512 -0.1130 0.6583 0.6712
1.750 0.6707 0.01098 0.00509 -0.1135 0.6553 0.6724
2.000 0.7006 0.01100 0.00508 -0.1142 0.6524 0.6737
2.250 0.7273 0.01096 0.00509 -0.1142 0.6480 0.6751
2.500 0.7544 0.01080 0.00491 -0.1142 0.6408 0.6766
2.750 0.7814 0.01071 0.00481 -0.1142 0.6339 0.6782
3.000 0.8086 0.01066 0.00478 -0.1143 0.6286 0.6800
3.250 0.8372 0.01064 0.00471 -0.1147 0.6235 0.6817
3.500 0.8628 0.01057 0.00472 -0.1145 0.6175 0.6831
3.750 0.8891 0.01051 0.00468 -0.1144 0.6111 0.6844
4.000 0.9150 0.01049 0.00471 -0.1142 0.6045 0.6859
4.250 0.9404 0.01047 0.00472 -0.1140 0.5969 0.6874
4.500 0.9656 0.01047 0.00477 -0.1137 0.5886 0.6891
4.750 0.9885 0.01045 0.00476 -0.1129 0.5735 0.6909
5.000 1.0086 0.01049 0.00476 -0.1116 0.5486 0.6928
5.250 1.0295 0.01063 0.00484 -0.1105 0.5241 0.6949
5.500 1.0385 0.01110 0.00507 -0.1072 0.4710 0.6970
5.750 1.0262 0.01214 0.00573 -0.1000 0.3990 0.6990
6.000 1.0145 0.01329 0.00659 -0.0933 0.3380 0.7010
6.250 0.9967 0.01489 0.00781 -0.0862 0.2656 0.7031
6.500 0.9818 0.01659 0.00918 -0.0802 0.2001 0.7055
6.750 0.9772 0.01805 0.01043 -0.0761 0.1555 0.7079
7.000 0.9767 0.01948 0.01167 -0.0730 0.1208 0.7104
7.250 0.9767 0.02096 0.01299 -0.0700 0.0860 0.7127
7.500 0.9795 0.02238 0.01429 -0.0676 0.0579 0.7150
7.750 0.9861 0.02365 0.01550 -0.0657 0.0360 0.7176
8.000 0.9971 0.02471 0.01653 -0.0644 0.0308 0.7206
8.250 1.0113 0.02560 0.01744 -0.0634 0.0274 0.7238
8.500 1.0268 0.02642 0.01832 -0.0627 0.0249 0.7268
8.750 1.0411 0.02730 0.01926 -0.0618 0.0192 0.7296
9.000 1.0530 0.02837 0.02036 -0.0607 0.0171 0.7327
9.250 1.0659 0.02942 0.02143 -0.0598 0.0156 0.7363
9.500 1.0783 0.03053 0.02256 -0.0589 0.0132 0.7400
9.750 1.0917 0.03156 0.02365 -0.0581 0.0126 0.7435
10.000 1.1045 0.03265 0.02481 -0.0573 0.0119 0.7473
10.250 1.1171 0.03380 0.02601 -0.0565 0.0111 0.7516
10.500 1.1301 0.03495 0.02722 -0.0558 0.0104 0.7561
10.750 1.1430 0.03609 0.02844 -0.0551 0.0099 0.7604
11.000 1.1559 0.03728 0.02970 -0.0544 0.0095 0.7657
11.250 1.1699 0.03841 0.03089 -0.0539 0.0092 0.7713
11.500 1.1834 0.03955 0.03213 -0.0534 0.0088 0.7769
11.750 1.1968 0.04076 0.03342 -0.0529 0.0082 0.7835
12.000 1.2096 0.04201 0.03477 -0.0524 0.0071 0.7898
12.250 1.2196 0.04356 0.03638 -0.0518 0.0041 0.7972
12.500 1.2271 0.04534 0.03820 -0.0510 0.0037 0.8044
12.750 1.2365 0.04700 0.03993 -0.0504 0.0035 0.8131
13.000 1.2461 0.04860 0.04164 -0.0498 0.0034 0.8223
13.250 1.2559 0.05024 0.04339 -0.0493 0.0033 0.8331
13.500 1.2650 0.05192 0.04519 -0.0488 0.0032 0.8459
13.750 1.2731 0.05366 0.04707 -0.0481 0.0032 0.8617
14.000 1.2795 0.05541 0.04898 -0.0472 0.0031 0.8853
14.250 1.2795 0.05684 0.05062 -0.0450 0.0030 1.0000
14.500 1.2876 0.05900 0.05286 -0.0450 0.0030 1.0000
14.750 1.2957 0.06117 0.05513 -0.0450 0.0029 1.0000
15.000 1.3011 0.06368 0.05775 -0.0449 0.0029 1.0000
15.250 1.3067 0.06620 0.06036 -0.0450 0.0028 1.0000
15.500 1.3114 0.06886 0.06311 -0.0451 0.0028 1.0000
15.750 1.3140 0.07183 0.06619 -0.0452 0.0028 1.0000
16.000 1.3173 0.07478 0.06925 -0.0455 0.0028 1.0000
16.250 1.3185 0.07807 0.07265 -0.0459 0.0028 1.0000
16.500 1.3188 0.08152 0.07622 -0.0463 0.0027 1.0000
16.750 1.3189 0.08506 0.07988 -0.0470 0.0027 1.0000
17.000 1.3169 0.08900 0.08394 -0.0478 0.0027 1.0000
17.250 1.3143 0.09310 0.08817 -0.0487 0.0027 1.0000
17.500 1.3122 0.09721 0.09240 -0.0498 0.0027 1.0000
17.750 1.3082 0.10169 0.09701 -0.0512 0.0027 1.0000
18.000 1.3036 0.10633 0.10178 -0.0527 0.0027 1.0000
18.250 1.2991 0.11106 0.10666 -0.0544 0.0027 1.0000
18.500 1.2942 0.11594 0.11167 -0.0563 0.0027 1.0000
18.750 1.2883 0.12104 0.11691 -0.0585 0.0027 1.0000
19.000 1.2827 0.12614 0.12214 -0.0608 0.0027 1.0000
19.250 1.2769 0.13138 0.12751 -0.0634 0.0027 1.0000
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Polar data table (+)
Polar graphs
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