SD7084 (9.6%) (sd7084-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: SD7084 (9.6%) (sd7084-il) Reynolds number: 100,000 Max Cl/Cd: 49.24 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7084-il-100000.txt Download as CSV file: xf-sd7084-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SD7084 (9.6%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4184 0.09178 0.08701 -0.0283 1.0000 0.1111
-8.250 -0.4454 0.08922 0.08463 -0.0335 1.0000 0.1140
-8.000 -0.4790 0.08626 0.08176 -0.0394 1.0000 0.1147
-7.750 -0.4305 0.08218 0.07765 -0.0300 1.0000 0.1204
-7.500 -0.4408 0.07956 0.07513 -0.0300 1.0000 0.1241
-7.250 -0.4759 0.07638 0.07197 -0.0361 1.0000 0.1283
-7.000 -0.4725 0.07250 0.06816 -0.0337 1.0000 0.1309
-6.750 -0.4638 0.07028 0.06600 -0.0301 1.0000 0.1356
-6.500 -0.4906 0.06690 0.06242 -0.0338 1.0000 0.1437
-6.250 -0.4749 0.06415 0.05986 -0.0291 1.0000 0.1479
-6.000 -0.4845 0.06098 0.05650 -0.0304 1.0000 0.1585
-5.750 -0.4736 0.05891 0.05456 -0.0268 1.0000 0.1674
-5.500 -0.4705 0.05618 0.05181 -0.0252 1.0000 0.1783
-5.250 -0.4664 0.05342 0.04899 -0.0242 1.0000 0.1912
-5.000 -0.4600 0.05079 0.04630 -0.0230 1.0000 0.2051
-4.750 -0.4298 0.03519 0.02859 -0.0288 1.0000 0.0826
-4.500 -0.4094 0.03135 0.02381 -0.0270 1.0000 0.0721
-4.250 -0.3897 0.02863 0.02076 -0.0258 1.0000 0.0706
-4.000 -0.3685 0.02653 0.01827 -0.0246 1.0000 0.0701
-3.750 -0.3466 0.02536 0.01664 -0.0233 1.0000 0.0728
-3.500 -0.3236 0.02349 0.01450 -0.0223 1.0000 0.0745
-3.250 -0.3011 0.02203 0.01297 -0.0214 1.0000 0.0766
-3.000 -0.2791 0.02100 0.01188 -0.0203 1.0000 0.0801
-2.750 -0.2574 0.02020 0.01096 -0.0192 1.0000 0.0858
-2.500 -0.2373 0.01936 0.01024 -0.0181 1.0000 0.0969
-2.250 -0.2171 0.01855 0.00948 -0.0169 1.0000 0.1143
-2.000 -0.1968 0.01722 0.00874 -0.0160 0.9997 0.1895
-1.750 -0.1402 0.01445 0.00906 -0.0195 0.9998 1.0000
-1.500 -0.0882 0.01493 0.00908 -0.0250 0.9898 1.0000
-1.250 -0.0376 0.01539 0.00919 -0.0301 0.9796 1.0000
-1.000 0.0141 0.01581 0.00934 -0.0353 0.9696 1.0000
-0.750 0.0628 0.01609 0.00938 -0.0398 0.9581 1.0000
-0.500 0.1088 0.01629 0.00941 -0.0437 0.9459 1.0000
-0.250 0.1547 0.01642 0.00939 -0.0473 0.9335 1.0000
0.000 0.2015 0.01648 0.00934 -0.0510 0.9213 1.0000
0.250 0.2517 0.01642 0.00920 -0.0552 0.9097 1.0000
0.500 0.3099 0.01617 0.00888 -0.0607 0.9007 1.0000
0.750 0.3514 0.01593 0.00860 -0.0628 0.8871 1.0000
1.000 0.3898 0.01566 0.00830 -0.0641 0.8730 1.0000
1.250 0.4253 0.01534 0.00797 -0.0647 0.8584 1.0000
1.500 0.4568 0.01504 0.00764 -0.0644 0.8425 1.0000
1.750 0.4827 0.01482 0.00740 -0.0632 0.8233 1.0000
2.000 0.5109 0.01454 0.00710 -0.0622 0.8051 1.0000
2.250 0.5396 0.01423 0.00675 -0.0612 0.7869 1.0000
2.500 0.5635 0.01412 0.00660 -0.0596 0.7637 1.0000
2.750 0.5895 0.01400 0.00642 -0.0583 0.7413 1.0000
3.000 0.6145 0.01396 0.00630 -0.0569 0.7165 1.0000
3.250 0.6384 0.01405 0.00630 -0.0555 0.6897 1.0000
3.500 0.6621 0.01420 0.00635 -0.0541 0.6621 1.0000
3.750 0.6856 0.01442 0.00649 -0.0527 0.6341 1.0000
4.000 0.7089 0.01469 0.00665 -0.0514 0.6058 1.0000
4.250 0.7319 0.01502 0.00687 -0.0501 0.5779 1.0000
4.500 0.7548 0.01540 0.00714 -0.0489 0.5504 1.0000
4.750 0.7777 0.01581 0.00748 -0.0477 0.5240 1.0000
5.000 0.8007 0.01626 0.00781 -0.0466 0.4991 1.0000
5.250 0.8233 0.01674 0.00823 -0.0455 0.4744 1.0000
5.500 0.8459 0.01725 0.00870 -0.0444 0.4511 1.0000
5.750 0.8690 0.01780 0.00915 -0.0435 0.4299 1.0000
6.000 0.8914 0.01835 0.00975 -0.0424 0.4086 1.0000
6.250 0.9142 0.01893 0.01030 -0.0415 0.3890 1.0000
6.500 0.9371 0.01955 0.01086 -0.0406 0.3705 1.0000
6.750 0.9590 0.02016 0.01155 -0.0396 0.3516 1.0000
7.000 0.9810 0.02079 0.01223 -0.0385 0.3334 1.0000
7.250 1.0032 0.02144 0.01287 -0.0376 0.3160 1.0000
7.500 1.0244 0.02212 0.01359 -0.0365 0.2984 1.0000
7.750 1.0444 0.02276 0.01435 -0.0352 0.2799 1.0000
8.000 1.0640 0.02339 0.01502 -0.0339 0.2614 1.0000
8.250 1.0827 0.02403 0.01567 -0.0325 0.2426 1.0000
8.500 1.0980 0.02454 0.01635 -0.0306 0.2213 1.0000
8.750 1.1114 0.02501 0.01685 -0.0286 0.1991 1.0000
9.000 1.1213 0.02549 0.01735 -0.0261 0.1735 1.0000
9.250 1.1283 0.02620 0.01816 -0.0233 0.1407 1.0000
9.500 1.1292 0.02783 0.01959 -0.0200 0.1012 1.0000
9.750 1.1275 0.03012 0.02167 -0.0164 0.0743 1.0000
10.000 1.1277 0.03214 0.02363 -0.0130 0.0615 1.0000
10.250 1.1306 0.03433 0.02583 -0.0100 0.0540 1.0000
10.500 1.1375 0.03642 0.02796 -0.0077 0.0489 1.0000
10.750 1.1525 0.03937 0.03096 -0.0064 0.0453 1.0000
11.000 1.1637 0.04168 0.03354 -0.0046 0.0424 1.0000
11.250 1.1708 0.04387 0.03590 -0.0028 0.0399 1.0000
11.500 1.1795 0.04639 0.03848 -0.0015 0.0378 1.0000
11.750 1.1905 0.05117 0.04342 -0.0008 0.0362 1.0000
12.000 1.1871 0.05415 0.04673 0.0013 0.0359 1.0000
12.250 1.1794 0.05743 0.05032 0.0033 0.0357 1.0000
12.500 1.1688 0.06101 0.05420 0.0047 0.0357 1.0000
12.750 1.1561 0.06490 0.05836 0.0055 0.0357 1.0000
13.000 1.1398 0.06929 0.06301 0.0055 0.0357 1.0000
13.250 1.1234 0.07415 0.06810 0.0048 0.0359 1.0000
13.500 1.1049 0.07952 0.07369 0.0031 0.0360 1.0000
13.750 1.0854 0.08553 0.07989 0.0006 0.0361 1.0000
14.000 1.0677 0.09150 0.08608 -0.0025 0.0364 1.0000
14.250 1.0457 0.09825 0.09303 -0.0072 0.0367 1.0000
14.500 0.9999 0.11099 0.10610 -0.0177 0.0382 1.0000
14.750 0.9156 0.13901 0.13419 -0.0362 0.0453 1.0000
15.000 0.9060 0.14734 0.14249 -0.0400 0.0461 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SD7084 (9.6%) (sd7084-il)