S7075 (9%) (s7075-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S7075 (9%) (s7075-il) Reynolds number: 50,000 Max Cl/Cd: 38.83 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s7075-il-50000.txt Download as CSV file: xf-s7075-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S7075 (9%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3968 0.10380 0.09716 -0.0243 1.0000 0.2311
-7.750 -0.3745 0.09867 0.09202 -0.0224 1.0000 0.2417
-7.500 -0.4098 0.09970 0.09328 -0.0210 1.0000 0.2461
-7.250 -0.3884 0.09488 0.08845 -0.0192 1.0000 0.2587
-7.000 -0.3864 0.09191 0.08556 -0.0173 1.0000 0.2670
-6.750 -0.4172 0.09212 0.08596 -0.0145 1.0000 0.2751
-6.500 -0.4075 0.08865 0.08253 -0.0119 1.0000 0.2877
-6.250 -0.4082 0.08608 0.08005 -0.0095 1.0000 0.3005
-6.000 -0.4122 0.08382 0.07787 -0.0071 1.0000 0.3148
-5.750 -0.4171 0.08165 0.07580 -0.0046 1.0000 0.3307
-5.500 -0.4300 0.08004 0.07430 -0.0029 1.0000 0.3490
-5.250 -0.4251 0.07710 0.07142 0.0005 1.0000 0.3681
-5.000 -0.4244 0.07485 0.06922 0.0038 1.0000 0.3915
-4.250 -0.3479 0.04691 0.03931 -0.0468 1.0000 0.1431
-4.000 -0.3192 0.04192 0.03369 -0.0490 1.0000 0.1284
-3.750 -0.2950 0.03844 0.02998 -0.0495 1.0000 0.1236
-3.500 -0.2650 0.03488 0.02571 -0.0507 1.0000 0.1186
-3.250 -0.2357 0.03218 0.02240 -0.0511 1.0000 0.1175
-3.000 -0.2095 0.03033 0.02027 -0.0510 1.0000 0.1234
-2.750 -0.1820 0.02853 0.01804 -0.0508 1.0000 0.1313
-2.500 -0.1558 0.02707 0.01631 -0.0501 1.0000 0.1429
-2.250 -0.1317 0.02567 0.01500 -0.0494 1.0000 0.1654
-2.000 -0.1068 0.02432 0.01378 -0.0485 1.0000 0.2092
-1.750 -0.0771 0.02192 0.01248 -0.0484 1.0000 0.3832
-1.500 -0.0748 0.01915 0.01198 -0.0399 1.0000 1.0000
-1.250 -0.0492 0.01940 0.01150 -0.0402 1.0000 1.0000
-1.000 -0.0258 0.01969 0.01131 -0.0403 1.0000 1.0000
-0.750 -0.0032 0.02003 0.01127 -0.0402 1.0000 1.0000
-0.500 0.0188 0.02042 0.01134 -0.0401 1.0000 1.0000
-0.250 0.0402 0.02085 0.01151 -0.0399 1.0000 1.0000
0.000 0.0612 0.02133 0.01173 -0.0398 1.0000 1.0000
0.250 0.0817 0.02185 0.01206 -0.0396 1.0000 1.0000
0.500 0.1018 0.02243 0.01247 -0.0395 1.0000 1.0000
0.750 0.1213 0.02307 0.01296 -0.0394 1.0000 1.0000
1.000 0.1404 0.02376 0.01351 -0.0393 1.0000 1.0000
1.250 0.1590 0.02451 0.01415 -0.0393 1.0000 1.0000
1.500 0.1770 0.02534 0.01489 -0.0393 1.0000 1.0000
1.750 0.1993 0.02632 0.01580 -0.0402 0.9976 1.0000
2.000 0.2538 0.02798 0.01737 -0.0469 0.9783 1.0000
2.250 0.3059 0.02945 0.01880 -0.0529 0.9587 1.0000
2.500 0.3530 0.03067 0.02001 -0.0576 0.9386 1.0000
2.750 0.3979 0.03171 0.02106 -0.0617 0.9176 1.0000
3.000 0.4482 0.03266 0.02206 -0.0663 0.8979 1.0000
3.250 0.4844 0.03334 0.02281 -0.0684 0.8753 1.0000
3.500 0.5360 0.03385 0.02343 -0.0724 0.8554 1.0000
3.750 0.5695 0.03428 0.02398 -0.0735 0.8321 1.0000
4.000 0.6241 0.03419 0.02406 -0.0770 0.8123 1.0000
4.250 0.6579 0.03428 0.02429 -0.0774 0.7879 1.0000
4.500 0.7068 0.03369 0.02394 -0.0792 0.7659 1.0000
4.750 0.7605 0.03251 0.02300 -0.0808 0.7436 1.0000
5.000 0.8067 0.03130 0.02201 -0.0810 0.7193 1.0000
5.250 0.8612 0.02938 0.02037 -0.0814 0.6941 1.0000
5.500 0.9058 0.02792 0.01908 -0.0806 0.6630 1.0000
5.750 0.9489 0.02660 0.01788 -0.0795 0.6265 1.0000
6.000 0.9794 0.02620 0.01746 -0.0774 0.5845 1.0000
6.250 1.0069 0.02612 0.01725 -0.0751 0.5389 1.0000
6.500 1.0285 0.02649 0.01744 -0.0724 0.4905 1.0000
6.750 1.0469 0.02714 0.01792 -0.0696 0.4401 1.0000
7.000 1.0644 0.02804 0.01851 -0.0668 0.3895 1.0000
7.250 1.0789 0.02927 0.01950 -0.0641 0.3397 1.0000
7.500 1.0943 0.03075 0.02068 -0.0616 0.2938 1.0000
7.750 1.1109 0.03256 0.02227 -0.0596 0.2542 1.0000
8.000 1.1290 0.03446 0.02402 -0.0579 0.2221 1.0000
8.250 1.1491 0.03670 0.02624 -0.0566 0.1978 1.0000
8.500 1.1697 0.03884 0.02833 -0.0555 0.1785 1.0000
8.750 1.1909 0.04166 0.03139 -0.0544 0.1662 1.0000
9.000 1.2088 0.04464 0.03465 -0.0530 0.1567 1.0000
9.250 1.2295 0.04736 0.03741 -0.0523 0.1472 1.0000
9.500 1.2354 0.05069 0.04138 -0.0497 0.1422 1.0000
9.750 1.2452 0.05428 0.04536 -0.0479 0.1387 1.0000
10.000 1.2606 0.05803 0.04928 -0.0469 0.1356 1.0000
10.250 1.2640 0.06249 0.05408 -0.0450 0.1340 1.0000
10.500 1.2540 0.06688 0.05895 -0.0421 0.1335 1.0000
10.750 1.2387 0.07143 0.06391 -0.0393 0.1332 1.0000
11.000 1.2192 0.07612 0.06891 -0.0368 0.1333 1.0000
11.250 1.1977 0.08076 0.07376 -0.0346 0.1337 1.0000
11.500 1.1755 0.08579 0.07894 -0.0331 0.1342 1.0000
11.750 1.0557 0.10003 0.09335 -0.0398 0.1463 1.0000
12.000 1.0449 0.10756 0.10089 -0.0425 0.1479 1.0000
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Polar data table (+)
Polar graphs
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