LISSAMAN 7769 AIRFOIL (l7769-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LISSAMAN 7769 AIRFOIL (l7769-il) Reynolds number: 500,000 Max Cl/Cd: 113.72 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-l7769-il-500000.txt Download as CSV file: xf-l7769-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: LISSAMAN 7769 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4241 0.08811 0.08430 -0.0011 0.5155 0.0381
-8.000 -0.4306 0.08419 0.08040 -0.0040 0.5142 0.0381
-7.750 -0.4268 0.08040 0.07659 -0.0039 0.5123 0.0386
-7.500 -0.4169 0.07800 0.07416 -0.0047 0.5100 0.0389
-7.250 -0.4061 0.07555 0.07172 -0.0057 0.5084 0.0393
-7.000 -0.3955 0.07281 0.06899 -0.0075 0.5066 0.0398
-6.750 -0.3846 0.06976 0.06592 -0.0099 0.5048 0.0405
-6.500 -0.3730 0.06616 0.06228 -0.0131 0.5030 0.0418
-6.250 -0.3676 0.05550 0.05140 -0.0238 0.5024 0.0452
-6.000 -0.3497 0.05357 0.04942 -0.0241 0.5003 0.0456
-5.750 -0.3600 0.02713 0.02145 -0.0325 0.5013 0.0377
-5.500 -0.3391 0.02357 0.01739 -0.0324 0.4994 0.0376
-5.250 -0.3155 0.02119 0.01461 -0.0321 0.4974 0.0375
-5.000 -0.2900 0.01966 0.01276 -0.0318 0.4953 0.0376
-4.750 -0.2636 0.01856 0.01141 -0.0314 0.4931 0.0377
-4.500 -0.2365 0.01762 0.01030 -0.0311 0.4911 0.0379
-4.250 -0.2090 0.01691 0.00943 -0.0308 0.4888 0.0381
-4.000 -0.1824 0.01565 0.00802 -0.0305 0.4865 0.0386
-3.750 -0.1552 0.01484 0.00715 -0.0302 0.4844 0.0394
-3.500 -0.1276 0.01437 0.00664 -0.0299 0.4824 0.0403
-3.250 -0.0999 0.01396 0.00615 -0.0296 0.4806 0.0410
-3.000 -0.0722 0.01361 0.00574 -0.0293 0.4786 0.0417
-2.750 -0.0443 0.01332 0.00539 -0.0291 0.4766 0.0426
-2.500 -0.0163 0.01299 0.00504 -0.0288 0.4750 0.0434
-2.250 0.0118 0.01272 0.00475 -0.0285 0.4731 0.0443
-2.000 0.0396 0.01232 0.00436 -0.0283 0.4711 0.0458
-1.750 0.0676 0.01208 0.00412 -0.0280 0.4690 0.0478
-1.500 0.0958 0.01191 0.00393 -0.0278 0.4670 0.0506
-1.250 0.1239 0.01170 0.00373 -0.0276 0.4653 0.0549
-1.000 0.1520 0.01155 0.00360 -0.0273 0.4636 0.0634
-0.750 0.1801 0.01148 0.00361 -0.0271 0.4618 0.0860
-0.500 0.2085 0.01152 0.00370 -0.0270 0.4602 0.1012
-0.250 0.2371 0.01152 0.00373 -0.0269 0.4586 0.1103
0.000 0.2657 0.01155 0.00380 -0.0268 0.4569 0.1187
0.250 0.2942 0.01154 0.00381 -0.0267 0.4552 0.1260
0.500 0.3227 0.01155 0.00384 -0.0266 0.4534 0.1336
0.750 0.3511 0.01152 0.00381 -0.0265 0.4515 0.1413
1.000 0.3795 0.01151 0.00381 -0.0264 0.4498 0.1495
1.250 0.4078 0.01148 0.00379 -0.0263 0.4483 0.1586
1.500 0.4361 0.01153 0.00383 -0.0262 0.4468 0.1677
1.750 0.4640 0.01161 0.00394 -0.0261 0.4450 0.1792
2.000 0.4924 0.01155 0.00397 -0.0260 0.4438 0.1914
2.250 0.5206 0.01149 0.00403 -0.0259 0.4423 0.2118
2.500 0.5598 0.00952 0.00414 -0.0285 0.4403 1.0000
2.750 0.5874 0.00962 0.00420 -0.0282 0.4385 1.0000
3.000 0.6151 0.00972 0.00427 -0.0280 0.4368 1.0000
3.250 0.6428 0.00980 0.00430 -0.0278 0.4349 1.0000
3.500 0.6706 0.00984 0.00428 -0.0275 0.4326 1.0000
3.750 0.6982 0.00998 0.00435 -0.0273 0.4301 1.0000
4.000 0.7259 0.01007 0.00446 -0.0271 0.4278 1.0000
4.250 0.7537 0.01011 0.00453 -0.0269 0.4251 1.0000
4.500 0.7816 0.01016 0.00459 -0.0267 0.4225 1.0000
4.750 0.8094 0.01023 0.00466 -0.0266 0.4203 1.0000
5.000 0.8373 0.01031 0.00473 -0.0264 0.4183 1.0000
5.250 0.8651 0.01039 0.00477 -0.0263 0.4160 1.0000
5.500 0.8928 0.01049 0.00488 -0.0261 0.4127 1.0000
5.750 0.9206 0.01046 0.00490 -0.0260 0.4088 1.0000
6.000 0.9485 0.01048 0.00495 -0.0258 0.4055 1.0000
6.250 0.9763 0.01052 0.00499 -0.0257 0.4027 1.0000
6.500 1.0040 0.01061 0.00505 -0.0256 0.3996 1.0000
6.750 1.0316 0.01071 0.00523 -0.0255 0.3966 1.0000
7.000 1.0592 0.01077 0.00537 -0.0254 0.3931 1.0000
7.250 1.0869 0.01082 0.00545 -0.0253 0.3895 1.0000
7.500 1.1145 0.01086 0.00550 -0.0251 0.3857 1.0000
7.750 1.1420 0.01094 0.00564 -0.0250 0.3812 1.0000
8.000 1.1696 0.01095 0.00573 -0.0249 0.3751 1.0000
8.250 1.1968 0.01098 0.00575 -0.0248 0.3682 1.0000
8.500 1.2243 0.01101 0.00588 -0.0247 0.3593 1.0000
8.750 1.2514 0.01110 0.00600 -0.0246 0.3490 1.0000
9.000 1.2782 0.01124 0.00617 -0.0245 0.3359 1.0000
9.250 1.3043 0.01148 0.00639 -0.0244 0.3163 1.0000
9.500 1.3281 0.01205 0.00682 -0.0242 0.2835 1.0000
9.750 1.3487 0.01308 0.00765 -0.0240 0.2450 1.0000
10.000 1.3688 0.01415 0.00859 -0.0237 0.2169 1.0000
10.250 1.3893 0.01511 0.00948 -0.0234 0.1971 1.0000
10.500 1.4095 0.01605 0.01037 -0.0231 0.1803 1.0000
10.750 1.4294 0.01696 0.01127 -0.0228 0.1641 1.0000
11.000 1.4476 0.01802 0.01228 -0.0225 0.1478 1.0000
11.250 1.4634 0.01925 0.01347 -0.0221 0.1322 1.0000
11.500 1.4754 0.02078 0.01496 -0.0217 0.1167 1.0000
11.750 1.4811 0.02290 0.01705 -0.0215 0.1014 1.0000
12.000 1.4744 0.02708 0.02129 -0.0236 0.0893 1.0000
12.250 1.4558 0.03120 0.02545 -0.0237 0.0818 1.0000
12.500 1.4378 0.03529 0.02952 -0.0236 0.0723 1.0000
12.750 1.4185 0.03955 0.03372 -0.0237 0.0606 1.0000
13.000 1.4001 0.04378 0.03790 -0.0238 0.0499 1.0000
13.250 1.3829 0.04802 0.04210 -0.0241 0.0407 1.0000
13.500 1.3698 0.05195 0.04601 -0.0245 0.0348 1.0000
13.750 1.3633 0.05544 0.04953 -0.0249 0.0317 1.0000
14.000 1.3573 0.05902 0.05314 -0.0255 0.0293 1.0000
14.250 1.3556 0.06222 0.05640 -0.0261 0.0277 1.0000
14.500 1.3516 0.06578 0.06000 -0.0268 0.0263 1.0000
14.750 1.3459 0.06965 0.06392 -0.0277 0.0252 1.0000
15.000 1.3447 0.07301 0.06736 -0.0285 0.0241 1.0000
15.250 1.3438 0.07640 0.07082 -0.0293 0.0235 1.0000
15.500 1.3418 0.08000 0.07448 -0.0303 0.0226 1.0000
15.750 1.3381 0.08390 0.07845 -0.0315 0.0220 1.0000
16.000 1.3331 0.08807 0.08267 -0.0328 0.0215 1.0000
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