74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: 74-130 WP2 (fx74130wp2-il) Reynolds number: 100,000 Max Cl/Cd: 36.5 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74130wp2-il-100000-n5.txt Download as CSV file: xf-fx74130wp2-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: 74-130 WP2
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1707 0.10392 0.09835 -0.0945 0.8495 0.0458
-10.250 -0.1663 0.10069 0.09513 -0.0963 0.8476 0.0470
-10.000 -0.1627 0.09752 0.09197 -0.0983 0.8458 0.0482
-9.750 -0.1626 0.09428 0.08875 -0.1008 0.8433 0.0497
-9.500 -0.1703 0.09122 0.08580 -0.1057 0.8405 0.0512
-9.250 -0.1735 0.08767 0.08230 -0.1097 0.8382 0.0515
-9.000 -0.1800 0.08374 0.07838 -0.1141 0.8358 0.0516
-8.500 -0.1976 0.07799 0.07253 -0.1166 0.8314 0.0518
-8.000 -0.1326 0.05262 0.04741 -0.1136 0.8236 0.0268
-7.750 -0.1399 0.04946 0.04424 -0.1129 0.8218 0.0261
-7.500 -0.1802 0.05982 0.05418 -0.1172 0.8230 0.0259
-7.250 -0.1791 0.05686 0.05108 -0.1169 0.8212 0.0252
-7.000 -0.1761 0.05386 0.04792 -0.1164 0.8196 0.0244
-6.750 -0.1718 0.05090 0.04478 -0.1158 0.8177 0.0237
-6.500 -0.1667 0.04803 0.04169 -0.1147 0.8151 0.0231
-6.250 -0.1590 0.04518 0.03857 -0.1135 0.8125 0.0223
-6.000 -0.1484 0.04243 0.03548 -0.1122 0.8104 0.0219
-5.750 -0.1350 0.03984 0.03252 -0.1110 0.8086 0.0215
-5.500 -0.1184 0.03788 0.03022 -0.1100 0.8071 0.0230
-5.250 -0.0996 0.03594 0.02787 -0.1091 0.8058 0.0241
-5.000 -0.0807 0.03416 0.02569 -0.1079 0.8040 0.0249
-4.750 -0.0645 0.03270 0.02392 -0.1064 0.8012 0.0249
-4.500 -0.0450 0.03121 0.02210 -0.1051 0.7990 0.0250
-4.250 -0.0235 0.02992 0.02049 -0.1041 0.7972 0.0252
-4.000 -0.0006 0.02876 0.01908 -0.1032 0.7956 0.0256
-3.750 0.0233 0.02774 0.01787 -0.1025 0.7942 0.0262
-3.500 0.0478 0.02687 0.01686 -0.1018 0.7928 0.0270
-3.250 0.0707 0.02584 0.01579 -0.1011 0.7915 0.0284
-3.000 0.0844 0.02565 0.01560 -0.0993 0.7887 0.0314
-2.750 0.0987 0.02566 0.01554 -0.0975 0.7859 0.0364
-2.500 0.1167 0.02534 0.01514 -0.0961 0.7834 0.0419
-2.250 0.1382 0.02498 0.01476 -0.0952 0.7814 0.0568
-2.000 0.1545 0.02353 0.01447 -0.0940 0.7797 0.3037
-1.500 0.1422 0.02389 0.01662 -0.0787 0.7736 0.8413
-1.250 0.1329 0.02458 0.01736 -0.0697 0.7695 0.8968
-1.000 0.2091 0.02492 0.01736 -0.0764 0.7706 0.9526
-0.750 0.2402 0.02517 0.01741 -0.0778 0.7687 0.9593
-0.500 0.2767 0.02533 0.01739 -0.0802 0.7672 0.9631
-0.250 0.3097 0.02546 0.01735 -0.0818 0.7657 0.9669
0.000 0.3393 0.02560 0.01735 -0.0827 0.7645 0.9709
0.500 0.3809 0.02683 0.01846 -0.0832 0.7565 0.9810
0.750 0.4084 0.02710 0.01865 -0.0840 0.7541 0.9847
1.000 0.4403 0.02727 0.01875 -0.0854 0.7523 0.9873
1.250 0.4724 0.02739 0.01881 -0.0867 0.7508 0.9900
1.750 0.4879 0.02879 0.02021 -0.0823 0.7402 1.0000
2.000 0.5076 0.02890 0.02029 -0.0811 0.7379 1.0000
2.250 0.5263 0.02904 0.02041 -0.0798 0.7356 1.0000
2.500 0.4884 0.02996 0.02134 -0.0697 0.7252 1.0000
2.750 0.5165 0.03006 0.02142 -0.0700 0.7234 1.0000
3.250 0.5366 0.03121 0.02258 -0.0660 0.7117 1.0000
3.500 0.5681 0.03129 0.02268 -0.0668 0.7098 1.0000
5.000 0.7045 0.03322 0.02493 -0.0655 0.6819 1.0000
5.250 0.7107 0.03413 0.02590 -0.0634 0.6715 1.0000
5.500 0.7451 0.03391 0.02583 -0.0644 0.6691 1.0000
5.750 0.7546 0.03466 0.02666 -0.0627 0.6587 1.0000
6.000 0.7891 0.03432 0.02645 -0.0635 0.6558 1.0000
6.500 0.8275 0.03481 0.02723 -0.0618 0.6393 1.0000
7.000 0.8669 0.03498 0.02768 -0.0600 0.6195 1.0000
8.000 0.9520 0.03369 0.02709 -0.0557 0.5636 1.0000
8.250 0.9723 0.03322 0.02676 -0.0542 0.5364 1.0000
8.500 1.0173 0.03040 0.02389 -0.0536 0.4824 1.0000
8.750 1.0494 0.02875 0.02144 -0.0514 0.3595 1.0000
9.000 1.0471 0.03053 0.02269 -0.0483 0.2812 1.0000
9.250 1.0452 0.03254 0.02423 -0.0457 0.2097 1.0000
9.500 1.0467 0.03447 0.02578 -0.0436 0.1501 1.0000
9.750 1.0498 0.03640 0.02737 -0.0417 0.1036 1.0000
10.000 1.0552 0.03824 0.02902 -0.0401 0.0752 1.0000
10.250 1.0615 0.04005 0.03078 -0.0385 0.0598 1.0000
10.500 1.0681 0.04188 0.03262 -0.0371 0.0498 1.0000
10.750 1.0730 0.04389 0.03462 -0.0357 0.0427 1.0000
11.000 1.0814 0.04566 0.03654 -0.0345 0.0362 1.0000
11.250 1.0863 0.04780 0.03871 -0.0332 0.0316 1.0000
11.500 1.0952 0.04967 0.04081 -0.0320 0.0278 1.0000
11.750 1.1023 0.05169 0.04289 -0.0311 0.0243 1.0000
12.000 1.1112 0.05379 0.04509 -0.0300 0.0218 1.0000
12.250 1.1245 0.05572 0.04723 -0.0289 0.0198 1.0000
12.500 1.1387 0.05774 0.04942 -0.0280 0.0185 1.0000
12.750 1.1500 0.05995 0.05178 -0.0272 0.0171 1.0000
13.000 1.1587 0.06249 0.05442 -0.0266 0.0159 1.0000
13.250 1.1674 0.06542 0.05762 -0.0258 0.0149 1.0000
13.500 1.1729 0.06839 0.06093 -0.0251 0.0141 1.0000
13.750 1.1750 0.07184 0.06471 -0.0244 0.0135 1.0000
14.000 1.1728 0.07579 0.06900 -0.0239 0.0132 1.0000
14.250 1.1666 0.08016 0.07369 -0.0236 0.0130 1.0000
14.500 1.1572 0.08486 0.07870 -0.0237 0.0128 1.0000
14.750 1.1449 0.09003 0.08417 -0.0242 0.0128 1.0000
15.000 1.1305 0.09565 0.09008 -0.0253 0.0127 1.0000
15.250 1.1144 0.10181 0.09650 -0.0271 0.0127 1.0000
15.500 1.0968 0.10856 0.10351 -0.0297 0.0127 1.0000
15.750 1.0783 0.11595 0.11113 -0.0332 0.0128 1.0000
16.000 1.0591 0.12412 0.11950 -0.0377 0.0130 1.0000
16.250 1.0388 0.13337 0.12894 -0.0433 0.0131 1.0000
16.500 1.0185 0.14368 0.13940 -0.0500 0.0134 1.0000
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Polar data table (+)
Polar graphs
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