WORTMANN FX 76-100 (fx76100-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 76-100 (fx76100-il) Reynolds number: 100,000 Max Cl/Cd: 36.18 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx76100-il-100000-n5.txt Download as CSV file: xf-fx76100-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 76-100
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.8048 0.08954 0.08394 -0.0191 1.0000 0.0321
-12.750 -0.8316 0.07996 0.07428 -0.0257 1.0000 0.0317
-12.500 -0.8574 0.07158 0.06576 -0.0318 1.0000 0.0313
-12.250 -0.8837 0.06453 0.05850 -0.0367 1.0000 0.0313
-12.000 -0.9034 0.05940 0.05317 -0.0389 1.0000 0.0311
-11.750 -0.9262 0.05495 0.04844 -0.0395 1.0000 0.0315
-11.500 -0.9436 0.05145 0.04466 -0.0382 1.0000 0.0317
-11.250 -0.9573 0.04855 0.04146 -0.0355 1.0000 0.0319
-11.000 -0.9635 0.04596 0.03868 -0.0329 1.0000 0.0326
-10.750 -0.9599 0.04386 0.03650 -0.0311 1.0000 0.0335
-10.500 -0.9552 0.04181 0.03428 -0.0291 1.0000 0.0342
-10.250 -0.9488 0.03977 0.03203 -0.0271 1.0000 0.0352
-10.000 -0.9402 0.03782 0.02984 -0.0252 1.0000 0.0365
-9.750 -0.9299 0.03594 0.02765 -0.0233 1.0000 0.0382
-9.500 -0.9179 0.03422 0.02554 -0.0213 1.0000 0.0402
-9.250 -0.9039 0.03242 0.02372 -0.0199 1.0000 0.0419
-9.000 -0.8883 0.03102 0.02224 -0.0184 1.0000 0.0436
-8.750 -0.8722 0.02972 0.02081 -0.0168 1.0000 0.0460
-8.500 -0.8550 0.02851 0.01934 -0.0152 1.0000 0.0492
-8.250 -0.8387 0.02712 0.01789 -0.0136 1.0000 0.0517
-8.000 -0.8219 0.02602 0.01675 -0.0120 1.0000 0.0547
-7.750 -0.8041 0.02502 0.01563 -0.0105 1.0000 0.0588
-7.500 -0.7871 0.02395 0.01450 -0.0087 1.0000 0.0630
-7.250 -0.7699 0.02302 0.01354 -0.0071 1.0000 0.0675
-7.000 -0.7516 0.02217 0.01256 -0.0054 1.0000 0.0735
-6.750 -0.7346 0.02127 0.01170 -0.0037 1.0000 0.0808
-6.500 -0.7168 0.02044 0.01086 -0.0020 1.0000 0.0897
-6.250 -0.6985 0.01968 0.01012 -0.0004 1.0000 0.1020
-6.000 -0.6801 0.01895 0.00947 0.0012 1.0000 0.1183
-5.750 -0.6611 0.01831 0.00887 0.0027 1.0000 0.1390
-5.500 -0.6419 0.01774 0.00839 0.0042 1.0000 0.1632
-5.250 -0.6223 0.01725 0.00796 0.0056 1.0000 0.1887
-5.000 -0.6024 0.01681 0.00755 0.0071 1.0000 0.2137
-4.750 -0.5827 0.01638 0.00719 0.0085 1.0000 0.2379
-4.500 -0.5627 0.01601 0.00686 0.0099 1.0000 0.2625
-4.250 -0.5430 0.01562 0.00655 0.0114 1.0000 0.2878
-4.000 -0.5234 0.01524 0.00628 0.0129 1.0000 0.3151
-3.750 -0.5038 0.01488 0.00601 0.0145 1.0000 0.3448
-3.500 -0.4843 0.01453 0.00579 0.0160 1.0000 0.3763
-3.250 -0.4648 0.01420 0.00559 0.0176 1.0000 0.4107
-3.000 -0.4454 0.01389 0.00541 0.0192 1.0000 0.4480
-2.750 -0.4261 0.01359 0.00529 0.0209 1.0000 0.4883
-2.500 -0.4066 0.01332 0.00521 0.0225 1.0000 0.5332
-2.250 -0.3868 0.01309 0.00518 0.0242 1.0000 0.5828
-2.000 -0.3662 0.01290 0.00518 0.0258 1.0000 0.6337
-1.750 -0.3432 0.01275 0.00524 0.0270 0.9997 0.6875
-1.500 -0.3007 0.01269 0.00538 0.0244 0.9917 0.7487
-1.250 -0.2568 0.01273 0.00554 0.0216 0.9844 0.8010
-1.000 -0.2102 0.01283 0.00569 0.0182 0.9772 0.8436
-0.750 -0.1596 0.01294 0.00582 0.0141 0.9693 0.8769
-0.500 -0.1071 0.01302 0.00590 0.0095 0.9599 0.9021
-0.250 -0.0543 0.01306 0.00594 0.0049 0.9490 0.9213
0.000 0.0001 0.01308 0.00595 0.0000 0.9368 0.9369
0.250 0.0546 0.01306 0.00594 -0.0050 0.9213 0.9491
0.500 0.1071 0.01302 0.00590 -0.0095 0.9020 0.9599
0.750 0.1596 0.01294 0.00582 -0.0141 0.8770 0.9692
1.000 0.2102 0.01283 0.00569 -0.0182 0.8439 0.9772
1.250 0.2570 0.01273 0.00554 -0.0216 0.8013 0.9845
1.500 0.3008 0.01269 0.00537 -0.0243 0.7474 0.9917
1.750 0.3432 0.01276 0.00524 -0.0270 0.6865 0.9998
2.250 0.3868 0.01309 0.00518 -0.0242 0.5829 1.0000
2.500 0.4066 0.01332 0.00522 -0.0225 0.5337 1.0000
2.750 0.4260 0.01359 0.00529 -0.0208 0.4880 1.0000
3.000 0.4453 0.01389 0.00541 -0.0192 0.4481 1.0000
3.250 0.4648 0.01420 0.00559 -0.0176 0.4107 1.0000
3.500 0.4843 0.01453 0.00579 -0.0160 0.3764 1.0000
3.750 0.5038 0.01488 0.00601 -0.0144 0.3449 1.0000
4.000 0.5234 0.01524 0.00626 -0.0129 0.3157 1.0000
4.250 0.5429 0.01562 0.00655 -0.0114 0.2881 1.0000
4.500 0.5626 0.01601 0.00686 -0.0099 0.2623 1.0000
4.750 0.5826 0.01639 0.00719 -0.0085 0.2377 1.0000
5.000 0.6023 0.01681 0.00756 -0.0070 0.2132 1.0000
5.250 0.6221 0.01725 0.00795 -0.0056 0.1884 1.0000
5.500 0.6419 0.01774 0.00839 -0.0042 0.1632 1.0000
5.750 0.6610 0.01832 0.00887 -0.0027 0.1390 1.0000
6.000 0.6800 0.01895 0.00947 -0.0012 0.1181 1.0000
6.250 0.6984 0.01968 0.01012 0.0004 0.1018 1.0000
6.500 0.7167 0.02044 0.01086 0.0020 0.0895 1.0000
6.750 0.7346 0.02128 0.01171 0.0037 0.0808 1.0000
7.000 0.7515 0.02218 0.01257 0.0054 0.0735 1.0000
7.250 0.7699 0.02303 0.01355 0.0071 0.0674 1.0000
7.500 0.7871 0.02396 0.01450 0.0088 0.0629 1.0000
7.750 0.8041 0.02502 0.01564 0.0105 0.0587 1.0000
8.000 0.8220 0.02601 0.01674 0.0120 0.0546 1.0000
8.250 0.8388 0.02713 0.01790 0.0136 0.0518 1.0000
8.500 0.8551 0.02851 0.01935 0.0152 0.0492 1.0000
8.750 0.8723 0.02973 0.02082 0.0168 0.0461 1.0000
9.000 0.8885 0.03103 0.02225 0.0183 0.0437 1.0000
9.250 0.9040 0.03245 0.02375 0.0199 0.0419 1.0000
9.500 0.9183 0.03429 0.02560 0.0213 0.0403 1.0000
9.750 0.9304 0.03603 0.02773 0.0232 0.0386 1.0000
10.000 0.9404 0.03789 0.02992 0.0252 0.0367 1.0000
10.250 0.9488 0.03984 0.03211 0.0271 0.0353 1.0000
10.500 0.9554 0.04187 0.03436 0.0291 0.0343 1.0000
10.750 0.9605 0.04381 0.03644 0.0310 0.0334 1.0000
11.000 0.9651 0.04580 0.03848 0.0327 0.0325 1.0000
11.250 0.9589 0.04845 0.04135 0.0354 0.0320 1.0000
11.500 0.9429 0.05138 0.04461 0.0381 0.0315 1.0000
11.750 0.9253 0.05491 0.04843 0.0394 0.0312 1.0000
12.000 0.9051 0.05920 0.05297 0.0388 0.0310 1.0000
12.250 0.8814 0.06485 0.05885 0.0361 0.0310 1.0000
12.500 0.8591 0.07145 0.06563 0.0317 0.0313 1.0000
12.750 0.8291 0.08069 0.07504 0.0248 0.0316 1.0000
13.000 0.8001 0.09094 0.08538 0.0176 0.0320 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 76-100 (fx76100-il)