FX 73-CL1-152 (fx73cl1152-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 73-CL1-152 (fx73cl1152-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.82 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx73cl1152-il-1000000-n5.txt Download as CSV file: xf-fx73cl1152-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 73-CL1-152
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5360 0.07146 0.06766 -0.0876 0.6324 0.0239
-13.750 -0.8022 0.02964 0.02547 -0.1256 0.6854 0.0236
-13.500 -0.7991 0.02660 0.02218 -0.1274 0.6644 0.0237
-13.250 -0.7871 0.02496 0.02035 -0.1276 0.6448 0.0237
-13.000 -0.7736 0.02346 0.01868 -0.1274 0.6275 0.0239
-12.500 -0.7373 0.02134 0.01629 -0.1268 0.5961 0.0244
-12.250 -0.7163 0.02058 0.01542 -0.1264 0.5814 0.0246
-12.000 -0.6944 0.01989 0.01461 -0.1259 0.5675 0.0248
-11.750 -0.6715 0.01929 0.01390 -0.1255 0.5536 0.0250
-11.500 -0.6480 0.01871 0.01322 -0.1251 0.5425 0.0252
-11.250 -0.6239 0.01821 0.01262 -0.1247 0.5316 0.0255
-11.000 -0.5993 0.01772 0.01204 -0.1243 0.5225 0.0258
-10.500 -0.5491 0.01684 0.01096 -0.1235 0.5052 0.0264
-10.250 -0.5238 0.01642 0.01044 -0.1231 0.4968 0.0266
-10.000 -0.4981 0.01601 0.00994 -0.1227 0.4899 0.0269
-9.750 -0.4721 0.01562 0.00947 -0.1223 0.4825 0.0271
-9.250 -0.4200 0.01484 0.00851 -0.1215 0.4688 0.0276
-9.000 -0.3938 0.01445 0.00806 -0.1212 0.4628 0.0279
-8.500 -0.3402 0.01385 0.00734 -0.1205 0.4529 0.0286
-8.250 -0.3130 0.01359 0.00703 -0.1202 0.4486 0.0290
-8.000 -0.2857 0.01334 0.00672 -0.1198 0.4441 0.0293
-7.750 -0.2585 0.01310 0.00642 -0.1195 0.4397 0.0297
-7.500 -0.2310 0.01288 0.00614 -0.1192 0.4362 0.0302
-7.250 -0.2033 0.01267 0.00588 -0.1189 0.4333 0.0306
-7.000 -0.1755 0.01248 0.00563 -0.1186 0.4297 0.0310
-6.750 -0.1481 0.01224 0.00534 -0.1183 0.4260 0.0314
-6.500 -0.1206 0.01202 0.00507 -0.1179 0.4221 0.0320
-6.250 -0.0928 0.01184 0.00486 -0.1176 0.4189 0.0325
-6.000 -0.0648 0.01165 0.00465 -0.1174 0.4169 0.0330
-5.750 -0.0367 0.01150 0.00446 -0.1171 0.4147 0.0336
-5.500 -0.0086 0.01135 0.00427 -0.1168 0.4122 0.0341
-5.250 0.0194 0.01121 0.00409 -0.1165 0.4098 0.0347
-5.000 0.0475 0.01109 0.00393 -0.1163 0.4073 0.0352
-4.750 0.0754 0.01094 0.00375 -0.1160 0.4047 0.0360
-4.250 0.1317 0.01070 0.00348 -0.1154 0.4001 0.0377
-4.000 0.1600 0.01059 0.00335 -0.1152 0.3984 0.0385
-3.750 0.1884 0.01049 0.00323 -0.1150 0.3965 0.0393
-3.500 0.2167 0.01040 0.00311 -0.1147 0.3946 0.0401
-3.250 0.2449 0.01029 0.00299 -0.1145 0.3927 0.0412
-3.000 0.2731 0.01021 0.00290 -0.1142 0.3907 0.0424
-2.750 0.3013 0.01015 0.00282 -0.1139 0.3885 0.0438
-2.500 0.3294 0.01011 0.00275 -0.1137 0.3860 0.0452
-2.250 0.3575 0.01005 0.00268 -0.1134 0.3837 0.0469
-2.000 0.3859 0.00998 0.00262 -0.1132 0.3825 0.0488
-1.750 0.4144 0.00992 0.00256 -0.1130 0.3808 0.0506
-1.500 0.4427 0.00987 0.00251 -0.1128 0.3788 0.0533
-1.250 0.4710 0.00983 0.00247 -0.1125 0.3768 0.0562
-1.000 0.4991 0.00979 0.00244 -0.1123 0.3747 0.0600
-0.750 0.5273 0.00977 0.00242 -0.1121 0.3726 0.0636
-0.500 0.5553 0.00976 0.00240 -0.1118 0.3704 0.0680
-0.250 0.5832 0.00976 0.00240 -0.1115 0.3679 0.0726
0.250 0.6396 0.00970 0.00240 -0.1111 0.3653 0.0861
0.500 0.6677 0.00967 0.00240 -0.1109 0.3640 0.0949
0.750 0.6958 0.00964 0.00241 -0.1107 0.3624 0.1070
1.000 0.7237 0.00962 0.00243 -0.1105 0.3605 0.1222
1.250 0.7515 0.00959 0.00246 -0.1102 0.3584 0.1422
1.500 0.7792 0.00958 0.00250 -0.1100 0.3562 0.1656
1.750 0.8069 0.00960 0.00255 -0.1097 0.3542 0.1844
2.000 0.8344 0.00962 0.00261 -0.1094 0.3521 0.2040
2.250 0.8619 0.00965 0.00268 -0.1092 0.3504 0.2234
2.500 0.8898 0.00965 0.00274 -0.1090 0.3492 0.2417
2.750 0.9176 0.00966 0.00280 -0.1088 0.3478 0.2610
3.000 0.9453 0.00968 0.00287 -0.1085 0.3461 0.2825
3.250 0.9726 0.00968 0.00295 -0.1083 0.3441 0.3164
3.500 0.9996 0.00964 0.00305 -0.1080 0.3418 0.3749
3.750 1.0260 0.00958 0.00317 -0.1076 0.3394 0.4558
4.000 1.0513 0.00947 0.00331 -0.1071 0.3370 0.5771
4.250 1.0739 0.00924 0.00348 -0.1059 0.3348 0.7490
4.750 1.1436 0.00903 0.00370 -0.1086 0.3315 1.0000
5.000 1.1709 0.00914 0.00380 -0.1083 0.3295 1.0000
5.250 1.1981 0.00925 0.00390 -0.1081 0.3272 1.0000
5.500 1.2250 0.00938 0.00401 -0.1078 0.3248 1.0000
5.750 1.2517 0.00953 0.00413 -0.1074 0.3224 1.0000
6.000 1.2780 0.00969 0.00427 -0.1071 0.3195 1.0000
6.250 1.3050 0.00981 0.00439 -0.1068 0.3177 1.0000
6.500 1.3318 0.00993 0.00452 -0.1065 0.3153 1.0000
6.750 1.3583 0.01007 0.00466 -0.1062 0.3126 1.0000
7.000 1.3845 0.01023 0.00480 -0.1059 0.3099 1.0000
7.250 1.4103 0.01040 0.00496 -0.1055 0.3072 1.0000
7.500 1.4356 0.01060 0.00514 -0.1050 0.3043 1.0000
7.750 1.4618 0.01074 0.00530 -0.1047 0.3025 1.0000
8.000 1.4877 0.01089 0.00547 -0.1043 0.3002 1.0000
8.250 1.5132 0.01106 0.00565 -0.1039 0.2974 1.0000
8.500 1.5382 0.01126 0.00584 -0.1034 0.2943 1.0000
8.750 1.5625 0.01149 0.00606 -0.1028 0.2911 1.0000
9.000 1.5870 0.01169 0.00627 -0.1023 0.2886 1.0000
9.250 1.6120 0.01187 0.00647 -0.1018 0.2865 1.0000
9.500 1.6364 0.01207 0.00669 -0.1013 0.2841 1.0000
9.750 1.6603 0.01229 0.00692 -0.1006 0.2816 1.0000
10.000 1.6835 0.01254 0.00718 -0.0999 0.2788 1.0000
10.250 1.7057 0.01282 0.00747 -0.0991 0.2758 1.0000
10.500 1.7287 0.01306 0.00773 -0.0984 0.2736 1.0000
10.750 1.7517 0.01328 0.00798 -0.0976 0.2717 1.0000
11.000 1.7739 0.01353 0.00826 -0.0968 0.2692 1.0000
11.250 1.7948 0.01383 0.00857 -0.0958 0.2659 1.0000
11.500 1.8128 0.01424 0.00897 -0.0944 0.2611 1.0000
11.750 1.8320 0.01453 0.00929 -0.0931 0.2566 1.0000
12.000 1.8474 0.01493 0.00969 -0.0912 0.2509 1.0000
12.250 1.8607 0.01544 0.01018 -0.0890 0.2461 1.0000
12.500 1.8783 0.01578 0.01056 -0.0876 0.2425 1.0000
12.750 1.8944 0.01620 0.01102 -0.0860 0.2388 1.0000
13.000 1.9071 0.01681 0.01162 -0.0841 0.2341 1.0000
13.250 1.9203 0.01744 0.01227 -0.0825 0.2282 1.0000
13.500 1.9301 0.01832 0.01314 -0.0806 0.2204 1.0000
13.750 1.9402 0.01929 0.01413 -0.0791 0.2129 1.0000
14.000 1.9442 0.02082 0.01563 -0.0775 0.2023 1.0000
14.250 1.9487 0.02252 0.01734 -0.0764 0.1931 1.0000
14.500 1.9498 0.02471 0.01954 -0.0756 0.1837 1.0000
14.750 1.9439 0.02774 0.02259 -0.0750 0.1742 1.0000
15.000 1.9313 0.03169 0.02656 -0.0748 0.1649 1.0000
15.250 1.9157 0.03609 0.03102 -0.0747 0.1566 1.0000
15.500 1.8900 0.04163 0.03662 -0.0747 0.1489 1.0000
15.750 1.8623 0.04741 0.04248 -0.0746 0.1429 1.0000
16.000 1.8362 0.05302 0.04817 -0.0746 0.1385 1.0000
16.250 1.8040 0.05943 0.05466 -0.0747 0.1329 1.0000
16.500 1.7734 0.06584 0.06113 -0.0751 0.1276 1.0000
16.750 1.7500 0.07150 0.06686 -0.0754 0.1229 1.0000
17.000 1.7256 0.07739 0.07280 -0.0759 0.1187 1.0000
17.250 1.7036 0.08303 0.07850 -0.0764 0.1136 1.0000
17.500 1.6761 0.08947 0.08497 -0.0772 0.1073 1.0000
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Polar data table (+)
Polar graphs
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