SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7080 (9.2%) (sd7080-il) Reynolds number: 100,000 Max Cl/Cd: 52.01 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7080-il-100000-n5.txt Download as CSV file: xf-sd7080-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7080 (9.2%)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4234 0.09153 0.08645 -0.0307 1.0000 0.0321
-8.750 -0.4240 0.08777 0.08275 -0.0321 1.0000 0.0318
-8.500 -0.4268 0.08385 0.07889 -0.0337 1.0000 0.0317
-8.250 -0.4320 0.07997 0.07510 -0.0353 1.0000 0.0317
-8.000 -0.4403 0.07632 0.07154 -0.0364 1.0000 0.0314
-7.750 -0.4501 0.07223 0.06754 -0.0384 1.0000 0.0309
-7.500 -0.4581 0.06737 0.06271 -0.0411 1.0000 0.0304
-7.250 -0.4655 0.06251 0.05782 -0.0429 1.0000 0.0303
-7.000 -0.4713 0.05771 0.05291 -0.0439 1.0000 0.0299
-6.750 -0.4744 0.05296 0.04799 -0.0443 1.0000 0.0296
-6.500 -0.4737 0.04835 0.04314 -0.0442 1.0000 0.0294
-6.250 -0.4695 0.04361 0.03803 -0.0440 1.0000 0.0288
-6.000 -0.4612 0.03894 0.03287 -0.0436 1.0000 0.0281
-5.750 -0.4485 0.03494 0.02832 -0.0429 1.0000 0.0277
-5.500 -0.4322 0.03184 0.02472 -0.0421 1.0000 0.0275
-5.250 -0.4138 0.02939 0.02181 -0.0412 1.0000 0.0276
-5.000 -0.3895 0.02722 0.01924 -0.0412 0.9987 0.0278
-4.750 -0.3555 0.02520 0.01685 -0.0429 0.9946 0.0283
-4.500 -0.3220 0.02353 0.01488 -0.0442 0.9902 0.0290
-4.250 -0.2875 0.02216 0.01328 -0.0457 0.9857 0.0303
-4.000 -0.2526 0.02119 0.01208 -0.0473 0.9811 0.0333
-3.750 -0.2194 0.02009 0.01087 -0.0484 0.9756 0.0354
-3.500 -0.1834 0.01909 0.00983 -0.0503 0.9710 0.0377
-3.250 -0.1513 0.01835 0.00899 -0.0512 0.9643 0.0411
-3.000 -0.1148 0.01762 0.00816 -0.0530 0.9588 0.0473
-2.750 -0.0815 0.01686 0.00746 -0.0542 0.9521 0.0684
-2.500 -0.0472 0.01594 0.00702 -0.0559 0.9458 0.1619
-2.250 -0.0151 0.01490 0.00684 -0.0574 0.9393 0.3471
-2.000 0.0150 0.01409 0.00677 -0.0578 0.9319 0.5388
-1.750 0.0442 0.01364 0.00673 -0.0573 0.9243 0.6744
-1.500 0.0731 0.01334 0.00665 -0.0564 0.9164 0.7776
-1.250 0.1047 0.01313 0.00652 -0.0560 0.9079 0.8660
-1.000 0.1591 0.01292 0.00623 -0.0606 0.9026 0.9510
-0.750 0.2096 0.01276 0.00591 -0.0651 0.8947 1.0000
-0.500 0.2413 0.01266 0.00565 -0.0656 0.8837 1.0000
-0.250 0.2708 0.01257 0.00543 -0.0657 0.8711 1.0000
0.000 0.2985 0.01251 0.00525 -0.0654 0.8571 1.0000
0.250 0.3264 0.01244 0.00508 -0.0651 0.8425 1.0000
0.500 0.3529 0.01240 0.00494 -0.0646 0.8259 1.0000
0.750 0.3800 0.01236 0.00482 -0.0641 0.8085 1.0000
1.000 0.4077 0.01232 0.00469 -0.0637 0.7905 1.0000
1.250 0.4360 0.01229 0.00456 -0.0633 0.7719 1.0000
1.500 0.4629 0.01231 0.00449 -0.0627 0.7507 1.0000
1.750 0.4904 0.01234 0.00442 -0.0622 0.7292 1.0000
2.000 0.5169 0.01242 0.00441 -0.0616 0.7055 1.0000
2.250 0.5434 0.01254 0.00440 -0.0609 0.6811 1.0000
2.500 0.5695 0.01269 0.00444 -0.0603 0.6564 1.0000
2.750 0.5950 0.01288 0.00454 -0.0596 0.6305 1.0000
3.000 0.6202 0.01310 0.00466 -0.0588 0.6046 1.0000
3.250 0.6453 0.01335 0.00480 -0.0581 0.5788 1.0000
3.500 0.6701 0.01362 0.00497 -0.0573 0.5534 1.0000
3.750 0.6947 0.01392 0.00520 -0.0566 0.5278 1.0000
4.000 0.7192 0.01423 0.00543 -0.0559 0.5022 1.0000
4.250 0.7434 0.01457 0.00569 -0.0551 0.4772 1.0000
4.500 0.7674 0.01494 0.00598 -0.0544 0.4528 1.0000
4.750 0.7913 0.01531 0.00633 -0.0536 0.4285 1.0000
5.000 0.8150 0.01571 0.00668 -0.0529 0.4048 1.0000
5.250 0.8384 0.01614 0.00704 -0.0521 0.3820 1.0000
5.500 0.8618 0.01657 0.00745 -0.0514 0.3589 1.0000
5.750 0.8849 0.01704 0.00792 -0.0506 0.3372 1.0000
6.000 0.9078 0.01752 0.00839 -0.0498 0.3153 1.0000
6.250 0.9303 0.01804 0.00889 -0.0490 0.2949 1.0000
6.500 0.9528 0.01857 0.00943 -0.0482 0.2742 1.0000
6.750 0.9746 0.01915 0.00999 -0.0474 0.2549 1.0000
7.000 0.9965 0.01974 0.01064 -0.0465 0.2353 1.0000
7.250 1.0178 0.02037 0.01130 -0.0456 0.2166 1.0000
7.500 1.0382 0.02106 0.01198 -0.0447 0.1984 1.0000
7.750 1.0587 0.02176 0.01272 -0.0437 0.1806 1.0000
8.000 1.0786 0.02250 0.01351 -0.0427 0.1631 1.0000
8.250 1.0978 0.02330 0.01439 -0.0416 0.1473 1.0000
8.500 1.1163 0.02416 0.01530 -0.0405 0.1328 1.0000
8.750 1.1341 0.02508 0.01629 -0.0392 0.1196 1.0000
9.000 1.1509 0.02606 0.01734 -0.0379 0.1063 1.0000
9.250 1.1663 0.02711 0.01843 -0.0365 0.0928 1.0000
9.500 1.1806 0.02821 0.01949 -0.0351 0.0766 1.0000
9.750 1.1947 0.02933 0.02069 -0.0338 0.0610 1.0000
10.000 1.2057 0.03069 0.02211 -0.0320 0.0502 1.0000
10.250 1.2124 0.03224 0.02369 -0.0297 0.0422 1.0000
10.500 1.2170 0.03387 0.02542 -0.0273 0.0351 1.0000
10.750 1.2189 0.03573 0.02739 -0.0247 0.0304 1.0000
11.000 1.2202 0.03765 0.02944 -0.0225 0.0268 1.0000
11.250 1.2154 0.04013 0.03198 -0.0203 0.0248 1.0000
11.500 1.2146 0.04248 0.03456 -0.0185 0.0233 1.0000
11.750 1.2128 0.04503 0.03731 -0.0172 0.0223 1.0000
12.000 1.2095 0.04789 0.04036 -0.0162 0.0212 1.0000
12.250 1.2055 0.05100 0.04364 -0.0157 0.0205 1.0000
12.500 1.2005 0.05440 0.04721 -0.0157 0.0198 1.0000
12.750 1.1947 0.05813 0.05110 -0.0162 0.0194 1.0000
13.000 1.1879 0.06221 0.05533 -0.0171 0.0190 1.0000
13.250 1.1798 0.06672 0.05999 -0.0184 0.0186 1.0000
13.500 1.1713 0.07147 0.06493 -0.0199 0.0183 1.0000
13.750 1.1626 0.07655 0.07017 -0.0219 0.0181 1.0000
14.000 1.1529 0.08206 0.07589 -0.0243 0.0179 1.0000
14.250 1.1422 0.08797 0.08201 -0.0272 0.0178 1.0000
14.500 1.1291 0.09465 0.08891 -0.0308 0.0176 1.0000
14.750 1.1152 0.10178 0.09623 -0.0347 0.0176 1.0000
15.000 1.1007 0.10938 0.10401 -0.0391 0.0176 1.0000
15.250 1.0851 0.11757 0.11237 -0.0439 0.0177 1.0000
15.500 1.0693 0.12618 0.12113 -0.0490 0.0178 1.0000
15.750 1.0518 0.13571 0.13076 -0.0548 0.0179 1.0000
16.000 1.0352 0.14545 0.14061 -0.0605 0.0181 1.0000
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Polar data table (+)
Polar graphs
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