FX 74-130 WP1 (fx74130wp1-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 74-130 WP1 (fx74130wp1-il) Reynolds number: 200,000 Max Cl/Cd: 72.01 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx74130wp1-il-200000.txt Download as CSV file: xf-fx74130wp1-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1623 0.11026 0.10650 -0.1080 0.9564 0.0352
-11.250 -0.1573 0.10675 0.10299 -0.1137 0.9529 0.0360
-11.000 -0.1491 0.10303 0.09927 -0.1186 0.9500 0.0363
-10.750 -0.1396 0.09914 0.09537 -0.1232 0.9476 0.0364
-10.250 -0.1183 0.08949 0.08569 -0.1263 0.9444 0.0382
-10.000 -0.1107 0.08675 0.08295 -0.1271 0.9410 0.0388
-9.750 -0.1023 0.08394 0.08013 -0.1283 0.9380 0.0400
-9.500 -0.0956 0.08075 0.07694 -0.1304 0.9351 0.0418
-9.250 -0.0901 0.07720 0.07339 -0.1334 0.9321 0.0435
-9.000 -0.0896 0.07377 0.06998 -0.1361 0.9285 0.0448
-8.750 -0.0946 0.07053 0.06676 -0.1381 0.9242 0.0453
-8.500 -0.1038 0.06649 0.06272 -0.1419 0.9194 0.0460
-8.250 -0.1191 0.06367 0.05986 -0.1429 0.9146 0.0467
-8.000 -0.1401 0.06222 0.05832 -0.1408 0.9089 0.0474
-7.750 -0.1547 0.06116 0.05698 -0.1393 0.9039 0.0482
-7.500 -0.1637 0.06027 0.05588 -0.1363 0.8997 0.0485
-7.250 -0.1798 0.05776 0.05328 -0.1322 0.8944 0.0489
-7.000 -0.1732 0.05285 0.04853 -0.1319 0.8921 0.0506
-6.750 -0.1607 0.05058 0.04624 -0.1315 0.8899 0.0522
-6.500 -0.1470 0.04830 0.04384 -0.1314 0.8879 0.0552
-6.250 -0.1768 0.04901 0.04456 -0.1223 0.8798 0.0552
-5.750 -0.1545 0.04395 0.03886 -0.1205 0.8747 0.0644
-5.500 -0.1981 0.04546 0.04037 -0.1080 0.8648 0.0640
-5.250 -0.1797 0.04345 0.03838 -0.1080 0.8629 0.0675
-5.000 -0.1557 0.04115 0.03576 -0.1089 0.8614 0.0794
-4.750 -0.1263 0.03905 0.03335 -0.1106 0.8603 0.0927
-3.250 -0.0541 0.02964 0.02186 -0.0906 0.8386 0.0354
-3.000 -0.0290 0.02864 0.02069 -0.0900 0.8363 0.0356
-2.750 0.0015 0.02783 0.01975 -0.0904 0.8345 0.0363
-2.500 0.0323 0.02661 0.01860 -0.0912 0.8332 0.0422
-2.250 0.0655 0.02599 0.01794 -0.0923 0.8322 0.0468
-2.000 0.0661 0.02645 0.01838 -0.0882 0.8271 0.0488
-1.750 0.0828 0.02628 0.01820 -0.0868 0.8233 0.0618
-1.500 0.0978 0.02359 0.01836 -0.0853 0.8216 0.7014
-1.250 0.1112 0.02445 0.01922 -0.0806 0.8191 0.8339
-1.000 0.1187 0.02485 0.01963 -0.0741 0.8173 0.8721
-0.750 0.0983 0.02564 0.02045 -0.0659 0.8091 0.8880
-0.500 0.0970 0.02568 0.02048 -0.0586 0.8057 0.9165
-0.250 0.2207 0.02648 0.02108 -0.0742 0.8082 0.9859
0.000 0.2689 0.02660 0.02107 -0.0788 0.8066 0.9890
0.250 0.3104 0.02666 0.02103 -0.0820 0.8051 0.9912
0.500 0.3514 0.02668 0.02096 -0.0849 0.8039 0.9928
0.750 0.3929 0.02669 0.02089 -0.0877 0.8030 0.9939
1.000 0.3872 0.02768 0.02189 -0.0840 0.7931 0.9999
1.250 0.4160 0.02770 0.02186 -0.0845 0.7909 1.0000
1.500 0.4497 0.02767 0.02180 -0.0857 0.7895 1.0000
1.750 0.4863 0.02765 0.02175 -0.0875 0.7884 1.0000
2.000 0.4436 0.02836 0.02247 -0.0760 0.7764 1.0000
2.250 0.4232 0.02885 0.02296 -0.0684 0.7669 1.0000
2.500 0.4466 0.02882 0.02291 -0.0678 0.7636 1.0000
2.750 0.4805 0.02868 0.02276 -0.0688 0.7617 1.0000
3.000 0.5177 0.02854 0.02263 -0.0704 0.7605 1.0000
3.250 0.5002 0.02907 0.02316 -0.0637 0.7492 1.0000
3.500 0.5379 0.02888 0.02298 -0.0653 0.7476 1.0000
3.750 0.5766 0.02868 0.02281 -0.0671 0.7462 1.0000
4.000 0.5798 0.02925 0.02339 -0.0642 0.7354 1.0000
4.250 0.6197 0.02892 0.02312 -0.0661 0.7339 1.0000
4.500 0.6610 0.02849 0.02274 -0.0682 0.7326 1.0000
4.750 0.6698 0.02907 0.02336 -0.0662 0.7218 1.0000
5.000 0.7120 0.02845 0.02284 -0.0682 0.7203 1.0000
5.250 0.7269 0.02887 0.02332 -0.0670 0.7104 1.0000
5.500 0.7702 0.02796 0.02251 -0.0690 0.7082 1.0000
5.750 0.8179 0.02671 0.02139 -0.0713 0.7069 1.0000
6.000 0.8381 0.02667 0.02144 -0.0704 0.6968 1.0000
6.250 0.8912 0.02460 0.01951 -0.0728 0.6950 1.0000
6.500 0.9547 0.02133 0.01641 -0.0758 0.6940 1.0000
6.750 0.9890 0.01971 0.01492 -0.0757 0.6830 1.0000
7.000 1.0304 0.01758 0.01290 -0.0762 0.6680 1.0000
7.250 1.0593 0.01672 0.01215 -0.0758 0.6464 1.0000
7.500 1.0852 0.01621 0.01167 -0.0750 0.6133 1.0000
7.750 1.1155 0.01549 0.01048 -0.0741 0.5178 1.0000
8.000 1.1081 0.01704 0.01141 -0.0692 0.4256 1.0000
8.250 1.0957 0.01914 0.01302 -0.0644 0.3469 1.0000
8.500 1.0835 0.02148 0.01487 -0.0601 0.2674 1.0000
8.750 1.0727 0.02398 0.01682 -0.0563 0.1832 1.0000
9.000 1.0645 0.02655 0.01883 -0.0530 0.1079 1.0000
9.250 1.0636 0.02877 0.02076 -0.0503 0.0756 1.0000
9.500 1.0691 0.03056 0.02251 -0.0485 0.0629 1.0000
9.750 1.0786 0.03209 0.02411 -0.0470 0.0559 1.0000
10.000 1.0852 0.03391 0.02591 -0.0453 0.0509 1.0000
10.250 1.0972 0.03540 0.02748 -0.0440 0.0469 1.0000
10.500 1.1109 0.03676 0.02890 -0.0430 0.0428 1.0000
10.750 1.1262 0.03847 0.03057 -0.0419 0.0394 1.0000
11.000 1.1472 0.03977 0.03200 -0.0413 0.0366 1.0000
11.250 1.1661 0.04106 0.03344 -0.0407 0.0335 1.0000
11.500 1.1876 0.04255 0.03494 -0.0403 0.0308 1.0000
11.750 1.2180 0.04470 0.03729 -0.0405 0.0276 1.0000
12.000 1.2393 0.04666 0.03951 -0.0399 0.0260 1.0000
12.250 1.2594 0.04908 0.04219 -0.0394 0.0245 1.0000
12.500 1.2756 0.05181 0.04517 -0.0386 0.0236 1.0000
12.750 1.2840 0.05458 0.04815 -0.0375 0.0227 1.0000
13.000 1.2920 0.05796 0.05170 -0.0367 0.0217 1.0000
13.250 1.2894 0.06366 0.05780 -0.0352 0.0211 1.0000
13.750 1.2591 0.07210 0.06687 -0.0313 0.0207 1.0000
14.000 1.2441 0.07667 0.07172 -0.0299 0.0207 1.0000
14.250 1.0951 0.07465 0.07030 -0.0181 0.0222 1.0000
14.500 1.0667 0.07902 0.07496 -0.0175 0.0223 1.0000
14.750 1.0430 0.08357 0.07974 -0.0178 0.0221 1.0000
15.000 0.9742 0.09444 0.09125 -0.0207 0.0246 1.0000
15.250 0.9428 0.10143 0.09848 -0.0240 0.0249 1.0000
15.500 0.9086 0.10967 0.10693 -0.0286 0.0264 1.0000
15.750 0.8784 0.11797 0.11539 -0.0340 0.0271 1.0000
16.000 0.8480 0.12724 0.12478 -0.0402 0.0277 1.0000
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