FX 61-184 AIRFOIL (fx61184-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-184 AIRFOIL (fx61184-il) Reynolds number: 500,000 Max Cl/Cd: 104.88 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61184-il-500000.txt Download as CSV file: xf-fx61184-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-184 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
------ -------- --------- --------- -------- -------- --------
-16.000 -0.5999 0.09898 0.09621 -0.0647 1.0000 0.0121
-15.750 -0.6348 0.08793 0.08496 -0.0714 1.0000 0.0121
-15.500 -0.6603 0.07965 0.07651 -0.0761 1.0000 0.0121
-15.250 -0.6855 0.07211 0.06874 -0.0804 1.0000 0.0121
-15.000 -0.7030 0.06637 0.06287 -0.0828 1.0000 0.0120
-14.750 -0.7203 0.06115 0.05744 -0.0852 1.0000 0.0122
-14.500 -0.7409 0.05595 0.05202 -0.0869 1.0000 0.0123
-14.250 -0.7496 0.05251 0.04843 -0.0874 1.0000 0.0123
-14.000 -0.7612 0.04876 0.04455 -0.0875 1.0000 0.0126
-13.750 -0.7366 0.04568 0.04144 -0.0926 0.9540 0.0130
-13.500 -0.7001 0.04237 0.03794 -0.1014 0.9318 0.0134
-13.250 -0.6576 0.03883 0.03410 -0.1112 0.9145 0.0140
-13.000 -0.6168 0.03588 0.03079 -0.1197 0.8931 0.0147
-12.750 -0.5935 0.03405 0.02856 -0.1244 0.8687 0.0154
-12.500 -0.5740 0.03220 0.02657 -0.1247 0.8556 0.0161
-12.250 -0.5579 0.03122 0.02552 -0.1255 0.8443 0.0167
-12.000 -0.5431 0.03034 0.02454 -0.1260 0.8351 0.0174
-11.750 -0.5278 0.02928 0.02334 -0.1257 0.8280 0.0180
-11.500 -0.5122 0.02831 0.02221 -0.1254 0.8217 0.0186
-11.250 -0.4979 0.02746 0.02119 -0.1253 0.8164 0.0191
-11.000 -0.4778 0.02643 0.02016 -0.1244 0.8118 0.0200
-10.750 -0.4615 0.02568 0.01939 -0.1240 0.8069 0.0208
-10.500 -0.4437 0.02499 0.01862 -0.1236 0.8024 0.0215
-10.250 -0.4268 0.02429 0.01787 -0.1230 0.7984 0.0224
-10.000 -0.4096 0.02363 0.01714 -0.1222 0.7943 0.0230
-9.750 -0.3921 0.02304 0.01646 -0.1216 0.7903 0.0235
-9.500 -0.3787 0.02211 0.01551 -0.1202 0.7865 0.0247
-9.250 -0.3642 0.02140 0.01479 -0.1193 0.7831 0.0254
-9.000 -0.3504 0.02069 0.01407 -0.1181 0.7792 0.0262
-8.750 -0.3366 0.01999 0.01333 -0.1170 0.7757 0.0270
-8.500 -0.3228 0.01931 0.01259 -0.1158 0.7724 0.0279
-8.250 -0.3064 0.01877 0.01198 -0.1150 0.7691 0.0289
-8.000 -0.3047 0.01771 0.01092 -0.1123 0.7656 0.0301
-7.750 -0.2985 0.01699 0.01021 -0.1101 0.7621 0.0314
-7.500 -0.2833 0.01635 0.00953 -0.1094 0.7588 0.0331
-7.250 -0.2650 0.01575 0.00886 -0.1091 0.7558 0.0351
-7.000 -0.2478 0.01500 0.00806 -0.1089 0.7527 0.0386
-6.750 -0.2265 0.01454 0.00759 -0.1086 0.7498 0.0432
-6.500 -0.2056 0.01393 0.00700 -0.1084 0.7466 0.0526
-6.250 -0.1837 0.01323 0.00641 -0.1085 0.7434 0.0744
-6.000 -0.1622 0.01217 0.00569 -0.1091 0.7405 0.1491
-5.750 -0.1384 0.01057 0.00475 -0.1111 0.7377 0.3092
-5.500 -0.1096 0.00952 0.00424 -0.1130 0.7350 0.4439
-5.250 -0.0802 0.00936 0.00426 -0.1136 0.7321 0.4998
-5.000 -0.0503 0.00941 0.00427 -0.1141 0.7290 0.5257
-4.750 -0.0204 0.00953 0.00435 -0.1145 0.7261 0.5428
-4.500 0.0100 0.00969 0.00442 -0.1150 0.7236 0.5553
-4.250 0.0395 0.00994 0.00464 -0.1152 0.7209 0.5642
-4.000 0.0682 0.01024 0.00494 -0.1151 0.7180 0.5758
-3.750 0.0970 0.01058 0.00527 -0.1151 0.7148 0.5858
-3.500 0.1256 0.01069 0.00537 -0.1151 0.7117 0.5905
-3.250 0.1545 0.01078 0.00543 -0.1153 0.7087 0.5936
-3.000 0.1841 0.01086 0.00544 -0.1156 0.7059 0.5969
-2.750 0.2138 0.01092 0.00543 -0.1161 0.7029 0.6006
-2.500 0.2432 0.01089 0.00535 -0.1166 0.6994 0.6038
-2.250 0.2717 0.01085 0.00531 -0.1168 0.6960 0.6059
-2.000 0.3006 0.01085 0.00530 -0.1170 0.6929 0.6078
-1.750 0.3301 0.01088 0.00528 -0.1174 0.6899 0.6100
-1.500 0.3591 0.01092 0.00529 -0.1177 0.6867 0.6124
-1.250 0.3879 0.01091 0.00527 -0.1181 0.6830 0.6152
-1.000 0.4176 0.01088 0.00521 -0.1186 0.6793 0.6178
-0.750 0.4477 0.01085 0.00511 -0.1192 0.6759 0.6201
-0.500 0.4770 0.01083 0.00505 -0.1196 0.6727 0.6218
-0.250 0.5047 0.01080 0.00507 -0.1197 0.6687 0.6234
0.000 0.5331 0.01078 0.00506 -0.1199 0.6643 0.6252
0.250 0.5622 0.01076 0.00502 -0.1202 0.6605 0.6270
0.500 0.5920 0.01078 0.00499 -0.1208 0.6569 0.6289
0.750 0.6202 0.01076 0.00500 -0.1210 0.6525 0.6311
1.000 0.6491 0.01074 0.00496 -0.1214 0.6479 0.6332
1.250 0.6788 0.01073 0.00491 -0.1219 0.6439 0.6350
1.500 0.7081 0.01072 0.00488 -0.1224 0.6399 0.6368
1.750 0.7355 0.01068 0.00490 -0.1225 0.6347 0.6384
2.000 0.7637 0.01066 0.00489 -0.1226 0.6298 0.6399
2.250 0.7925 0.01069 0.00488 -0.1230 0.6252 0.6414
2.500 0.8199 0.01068 0.00494 -0.1230 0.6193 0.6430
2.750 0.8480 0.01069 0.00495 -0.1232 0.6140 0.6449
3.000 0.8765 0.01074 0.00498 -0.1235 0.6088 0.6469
3.250 0.9041 0.01075 0.00503 -0.1237 0.6021 0.6488
3.500 0.9323 0.01079 0.00501 -0.1239 0.5956 0.6505
3.750 0.9595 0.01082 0.00507 -0.1240 0.5876 0.6520
4.000 0.9866 0.01082 0.00507 -0.1240 0.5804 0.6537
4.250 1.0132 0.01086 0.00517 -0.1239 0.5734 0.6553
4.500 1.0398 0.01094 0.00526 -0.1239 0.5664 0.6570
4.750 1.0664 0.01102 0.00538 -0.1238 0.5591 0.6586
5.000 1.0929 0.01112 0.00549 -0.1237 0.5517 0.6603
5.250 1.1192 0.01123 0.00562 -0.1237 0.5443 0.6621
5.500 1.1451 0.01135 0.00574 -0.1235 0.5357 0.6639
5.750 1.1708 0.01148 0.00589 -0.1233 0.5267 0.6658
6.250 1.2205 0.01176 0.00620 -0.1227 0.5072 0.6694
6.500 1.2443 0.01192 0.00639 -0.1221 0.4976 0.6712
6.750 1.2672 0.01212 0.00659 -0.1214 0.4869 0.6728
7.000 1.2900 0.01230 0.00683 -0.1207 0.4752 0.6746
7.250 1.3112 0.01254 0.00707 -0.1198 0.4617 0.6764
7.500 1.3310 0.01283 0.00734 -0.1185 0.4463 0.6784
7.750 1.3491 0.01316 0.00765 -0.1170 0.4294 0.6804
8.000 1.3633 0.01359 0.00802 -0.1149 0.4096 0.6823
8.250 1.3733 0.01406 0.00841 -0.1120 0.3889 0.6842
8.500 1.3824 0.01457 0.00888 -0.1090 0.3677 0.6863
8.750 1.3896 0.01522 0.00948 -0.1058 0.3477 0.6883
9.000 1.3956 0.01597 0.01018 -0.1026 0.3271 0.6903
9.250 1.4008 0.01683 0.01099 -0.0995 0.3062 0.6924
9.500 1.4035 0.01788 0.01197 -0.0964 0.2864 0.6946
9.750 1.4056 0.01909 0.01312 -0.0934 0.2673 0.6968
10.000 1.4084 0.02040 0.01436 -0.0909 0.2476 0.6989
10.250 1.4113 0.02181 0.01572 -0.0885 0.2301 0.7010
10.500 1.4138 0.02333 0.01720 -0.0864 0.2127 0.7031
10.750 1.4161 0.02495 0.01878 -0.0843 0.1958 0.7054
11.000 1.4176 0.02671 0.02049 -0.0824 0.1796 0.7079
11.250 1.4207 0.02843 0.02218 -0.0807 0.1650 0.7106
11.500 1.4225 0.03032 0.02400 -0.0791 0.1489 0.7131
11.750 1.4252 0.03221 0.02583 -0.0776 0.1336 0.7155
12.000 1.4267 0.03421 0.02780 -0.0762 0.1186 0.7178
12.250 1.4277 0.03633 0.02989 -0.0748 0.1046 0.7202
12.500 1.4287 0.03853 0.03206 -0.0736 0.0919 0.7228
12.750 1.4296 0.04083 0.03434 -0.0725 0.0799 0.7255
13.000 1.4302 0.04327 0.03674 -0.0716 0.0690 0.7283
13.250 1.4305 0.04584 0.03930 -0.0708 0.0601 0.7311
13.500 1.4331 0.04824 0.04173 -0.0702 0.0533 0.7341
13.750 1.4349 0.05082 0.04435 -0.0697 0.0477 0.7372
14.000 1.4374 0.05341 0.04698 -0.0693 0.0432 0.7408
14.250 1.4392 0.05617 0.04978 -0.0690 0.0396 0.7444
14.500 1.4438 0.05867 0.05235 -0.0689 0.0370 0.7480
14.750 1.4451 0.06161 0.05536 -0.0689 0.0347 0.7516
15.000 1.4452 0.06481 0.05863 -0.0690 0.0328 0.7554
15.250 1.4506 0.06740 0.06133 -0.0692 0.0315 0.7602
15.500 1.4543 0.07025 0.06429 -0.0695 0.0300 0.7649
15.750 1.4556 0.07348 0.06760 -0.0699 0.0286 0.7698
16.000 1.4535 0.07725 0.07145 -0.0705 0.0272 0.7753
16.250 1.4556 0.08052 0.07483 -0.0711 0.0262 0.7816
16.500 1.4598 0.08355 0.07800 -0.0718 0.0252 0.7894
16.750 1.4630 0.08675 0.08132 -0.0726 0.0242 0.7987
17.000 1.4645 0.09025 0.08494 -0.0735 0.0233 0.8105
17.250 1.4632 0.09422 0.08904 -0.0746 0.0224 0.8257
17.500 1.4578 0.09882 0.09379 -0.0759 0.0215 0.8476
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