SD7084 (9.6%) (sd7084-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7084 (9.6%) (sd7084-il) Reynolds number: 200,000 Max Cl/Cd: 63.8 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7084-il-200000-n5.txt Download as CSV file: xf-sd7084-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4426 0.11641 0.11269 -0.0188 1.0000 0.0205
-10.750 -0.4408 0.11213 0.10844 -0.0203 1.0000 0.0194
-10.500 -0.4415 0.10729 0.10362 -0.0223 1.0000 0.0181
-9.750 -0.4529 0.08998 0.08642 -0.0304 1.0000 0.0159
-9.500 -0.4586 0.08432 0.08083 -0.0333 1.0000 0.0161
-9.250 -0.4642 0.07924 0.07580 -0.0359 1.0000 0.0161
-8.750 -0.4805 0.06860 0.06526 -0.0422 1.0000 0.0159
-8.500 -0.4990 0.06282 0.05953 -0.0461 1.0000 0.0157
-8.250 -0.5202 0.05611 0.05272 -0.0476 1.0000 0.0158
-8.000 -0.5388 0.05131 0.04776 -0.0463 1.0000 0.0159
-7.750 -0.5543 0.04702 0.04323 -0.0439 1.0000 0.0160
-7.500 -0.5618 0.04185 0.03773 -0.0430 0.9983 0.0163
-7.250 -0.5419 0.03807 0.03365 -0.0456 0.9936 0.0170
-7.000 -0.5222 0.03387 0.02899 -0.0472 0.9882 0.0174
-6.750 -0.4976 0.03029 0.02493 -0.0487 0.9842 0.0178
-6.500 -0.4725 0.02760 0.02182 -0.0495 0.9799 0.0184
-6.250 -0.4461 0.02523 0.01904 -0.0500 0.9755 0.0190
-6.000 -0.4154 0.02348 0.01692 -0.0512 0.9722 0.0202
-5.750 -0.3828 0.02198 0.01509 -0.0525 0.9696 0.0216
-5.500 -0.3560 0.02050 0.01331 -0.0524 0.9643 0.0220
-5.250 -0.3240 0.01918 0.01176 -0.0533 0.9607 0.0225
-5.000 -0.2910 0.01783 0.01025 -0.0545 0.9578 0.0231
-4.750 -0.2634 0.01665 0.00899 -0.0546 0.9528 0.0242
-4.500 -0.2343 0.01586 0.00813 -0.0550 0.9477 0.0254
-4.250 -0.2017 0.01528 0.00749 -0.0560 0.9439 0.0276
-4.000 -0.1746 0.01477 0.00692 -0.0558 0.9374 0.0299
-3.750 -0.1450 0.01422 0.00627 -0.0561 0.9317 0.0315
-3.500 -0.1171 0.01361 0.00561 -0.0560 0.9256 0.0347
-3.250 -0.0898 0.01318 0.00512 -0.0558 0.9184 0.0408
-3.000 -0.0619 0.01271 0.00468 -0.0557 0.9120 0.0572
-2.750 -0.0362 0.01224 0.00435 -0.0552 0.9039 0.0937
-2.500 -0.0110 0.01168 0.00408 -0.0548 0.8959 0.1648
-2.250 0.0127 0.01090 0.00385 -0.0542 0.8877 0.3007
-2.000 0.0343 0.01027 0.00371 -0.0530 0.8775 0.4349
-1.750 0.0577 0.00981 0.00357 -0.0519 0.8678 0.5345
-1.500 0.0809 0.00937 0.00346 -0.0505 0.8582 0.6352
-1.250 0.1028 0.00901 0.00340 -0.0487 0.8462 0.7330
-1.000 0.1282 0.00876 0.00335 -0.0473 0.8339 0.8147
-0.750 0.1631 0.00862 0.00327 -0.0480 0.8211 0.8802
-0.500 0.2064 0.00856 0.00313 -0.0507 0.8066 0.9243
-0.250 0.2493 0.00852 0.00298 -0.0534 0.7897 0.9537
0.000 0.2905 0.00851 0.00284 -0.0559 0.7703 0.9737
0.250 0.3302 0.00851 0.00269 -0.0582 0.7483 0.9892
0.500 0.3685 0.00854 0.00256 -0.0604 0.7245 1.0000
0.750 0.3913 0.00862 0.00248 -0.0592 0.7013 1.0000
1.000 0.4142 0.00872 0.00244 -0.0581 0.6772 1.0000
1.250 0.4372 0.00886 0.00243 -0.0571 0.6529 1.0000
1.500 0.4602 0.00901 0.00244 -0.0560 0.6290 1.0000
1.750 0.4832 0.00919 0.00247 -0.0550 0.6046 1.0000
2.000 0.5064 0.00937 0.00253 -0.0540 0.5806 1.0000
2.250 0.5295 0.00957 0.00260 -0.0531 0.5569 1.0000
2.500 0.5526 0.00978 0.00270 -0.0521 0.5338 1.0000
2.750 0.5758 0.01000 0.00282 -0.0512 0.5105 1.0000
3.000 0.5989 0.01024 0.00295 -0.0502 0.4881 1.0000
3.250 0.6221 0.01048 0.00310 -0.0493 0.4658 1.0000
3.500 0.6453 0.01073 0.00326 -0.0485 0.4445 1.0000
3.750 0.6686 0.01100 0.00346 -0.0476 0.4233 1.0000
4.000 0.6918 0.01127 0.00366 -0.0468 0.4032 1.0000
4.250 0.7153 0.01155 0.00388 -0.0460 0.3835 1.0000
4.500 0.7385 0.01185 0.00411 -0.0451 0.3647 1.0000
4.750 0.7619 0.01215 0.00438 -0.0444 0.3473 1.0000
5.000 0.7853 0.01245 0.00465 -0.0436 0.3303 1.0000
5.250 0.8087 0.01276 0.00494 -0.0429 0.3143 1.0000
5.500 0.8320 0.01309 0.00524 -0.0421 0.2989 1.0000
5.750 0.8553 0.01342 0.00557 -0.0414 0.2844 1.0000
6.000 0.8784 0.01377 0.00594 -0.0406 0.2703 1.0000
6.250 0.9015 0.01413 0.00630 -0.0398 0.2568 1.0000
6.500 0.9243 0.01450 0.00669 -0.0391 0.2431 1.0000
6.750 0.9470 0.01489 0.00709 -0.0383 0.2296 1.0000
7.000 0.9695 0.01529 0.00751 -0.0375 0.2159 1.0000
7.250 0.9917 0.01570 0.00794 -0.0366 0.2017 1.0000
7.500 1.0135 0.01615 0.00844 -0.0357 0.1864 1.0000
7.750 1.0347 0.01664 0.00892 -0.0348 0.1698 1.0000
8.000 1.0550 0.01720 0.00944 -0.0338 0.1465 1.0000
8.250 1.0727 0.01800 0.01004 -0.0326 0.1144 1.0000
8.500 1.0895 0.01889 0.01076 -0.0312 0.0830 1.0000
8.750 1.1062 0.01978 0.01157 -0.0298 0.0621 1.0000
9.000 1.1206 0.02087 0.01258 -0.0281 0.0406 1.0000
9.250 1.1335 0.02205 0.01370 -0.0262 0.0252 1.0000
9.500 1.1451 0.02328 0.01493 -0.0241 0.0172 1.0000
9.750 1.1574 0.02436 0.01611 -0.0221 0.0140 1.0000
10.000 1.1674 0.02545 0.01731 -0.0197 0.0124 1.0000
10.250 1.1720 0.02679 0.01876 -0.0167 0.0112 1.0000
10.500 1.1791 0.02795 0.02008 -0.0142 0.0107 1.0000
10.750 1.1841 0.02929 0.02158 -0.0117 0.0102 1.0000
11.000 1.1879 0.03076 0.02320 -0.0093 0.0098 1.0000
11.250 1.1900 0.03242 0.02505 -0.0071 0.0093 1.0000
11.500 1.1913 0.03424 0.02701 -0.0051 0.0091 1.0000
11.750 1.1916 0.03624 0.02915 -0.0034 0.0089 1.0000
12.000 1.1908 0.03849 0.03153 -0.0021 0.0086 1.0000
12.250 1.1887 0.04100 0.03418 -0.0011 0.0084 1.0000
12.500 1.1863 0.04374 0.03706 -0.0005 0.0083 1.0000
12.750 1.1814 0.04692 0.04036 -0.0004 0.0080 1.0000
13.000 1.1765 0.05033 0.04390 -0.0005 0.0079 1.0000
13.250 1.1679 0.05441 0.04811 -0.0012 0.0076 1.0000
13.500 1.1615 0.05840 0.05223 -0.0020 0.0075 1.0000
13.750 1.1582 0.06221 0.05621 -0.0032 0.0074 1.0000
14.000 1.1539 0.06634 0.06053 -0.0047 0.0072 1.0000
14.250 1.1474 0.07095 0.06532 -0.0066 0.0070 1.0000
14.500 1.1399 0.07582 0.07034 -0.0085 0.0070 1.0000
14.750 1.1317 0.08107 0.07577 -0.0110 0.0069 1.0000
15.000 1.1231 0.08654 0.08139 -0.0136 0.0068 1.0000
15.250 1.1141 0.09225 0.08726 -0.0164 0.0068 1.0000
15.500 1.1037 0.09843 0.09361 -0.0196 0.0067 1.0000
15.750 1.0928 0.10490 0.10023 -0.0230 0.0067 1.0000
16.000 1.0814 0.11172 0.10720 -0.0267 0.0067 1.0000
16.250 1.0697 0.11880 0.11443 -0.0306 0.0067 1.0000
16.500 1.0570 0.12635 0.12213 -0.0348 0.0067 1.0000
16.750 1.0448 0.13407 0.12999 -0.0392 0.0067 1.0000
17.000 1.0318 0.14225 0.13832 -0.0440 0.0068 1.0000
17.250 1.0171 0.15127 0.14747 -0.0492 0.0068 1.0000
17.500 1.0029 0.16056 0.15688 -0.0546 0.0069 1.0000
17.750 0.9852 0.17155 0.16797 -0.0608 0.0070 1.0000
18.000 0.9645 0.18455 0.18104 -0.0678 0.0072 1.0000
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Polar data table (+)
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