E176 (8.83%) (e176-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E176 (8.83%) (e176-il) Reynolds number: 500,000 Max Cl/Cd: 110.71 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e176-il-500000.txt Download as CSV file: xf-e176-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: E176 (8.83%)
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 -0.3911 0.08480 0.08270 -0.0241 1.0000 0.0183
-8.000 -0.3894 0.08129 0.07922 -0.0260 1.0000 0.0188
-7.750 -0.3893 0.07784 0.07582 -0.0278 1.0000 0.0190
-7.500 -0.3923 0.07393 0.07196 -0.0307 1.0000 0.0198
-7.250 -0.3863 0.06887 0.06693 -0.0371 1.0000 0.0205
-7.000 -0.3606 0.06206 0.06006 -0.0482 0.9785 0.0210
-6.750 -0.3246 0.03828 0.03603 -0.0539 0.8651 0.0216
-6.500 -0.3213 0.03362 0.03122 -0.0553 0.8466 0.0223
-6.250 -0.3091 0.03089 0.02836 -0.0559 0.8307 0.0230
-6.000 -0.2950 0.02768 0.02499 -0.0571 0.8168 0.0239
-5.750 -0.2822 0.03718 0.03409 -0.0655 0.8393 0.0254
-5.500 -0.2551 0.03524 0.03167 -0.0655 0.8238 0.0294
-5.250 -0.2432 0.02810 0.02394 -0.0666 0.8109 0.0311
-5.000 -0.2208 0.02649 0.02225 -0.0667 0.7986 0.0324
-4.750 -0.1970 0.02520 0.02079 -0.0666 0.7870 0.0349
-4.500 -0.1666 0.02659 0.02186 -0.0658 0.7757 0.0402
-4.250 -0.1451 0.01656 0.01065 -0.0646 0.7684 0.0219
-4.000 -0.1185 0.01505 0.00894 -0.0641 0.7592 0.0204
-3.750 -0.0920 0.01348 0.00712 -0.0637 0.7505 0.0199
-3.500 -0.0653 0.01247 0.00591 -0.0632 0.7427 0.0201
-3.250 -0.0382 0.01172 0.00505 -0.0630 0.7344 0.0206
-3.000 -0.0112 0.01117 0.00437 -0.0627 0.7272 0.0210
-2.750 0.0157 0.01047 0.00359 -0.0624 0.7196 0.0219
-2.500 0.0428 0.00998 0.00298 -0.0622 0.7131 0.0239
-2.250 0.0706 0.00965 0.00260 -0.0621 0.7058 0.0254
-2.000 0.0983 0.00945 0.00228 -0.0619 0.6996 0.0285
-1.750 0.1259 0.00894 0.00198 -0.0618 0.6929 0.0831
-1.500 0.1526 0.00848 0.00184 -0.0618 0.6870 0.1912
-1.250 0.1792 0.00797 0.00178 -0.0619 0.6807 0.3331
-1.000 0.2052 0.00748 0.00175 -0.0618 0.6747 0.4873
-0.750 0.2290 0.00690 0.00176 -0.0611 0.6693 0.6806
-0.500 0.2484 0.00625 0.00181 -0.0585 0.6634 0.9112
-0.250 0.3017 0.00622 0.00169 -0.0639 0.6578 1.0000
0.000 0.3287 0.00626 0.00167 -0.0636 0.6518 1.0000
0.250 0.3556 0.00633 0.00165 -0.0634 0.6461 1.0000
0.500 0.3827 0.00641 0.00165 -0.0632 0.6408 1.0000
0.750 0.4100 0.00646 0.00166 -0.0631 0.6349 1.0000
1.000 0.4372 0.00656 0.00167 -0.0629 0.6296 1.0000
1.250 0.4647 0.00661 0.00171 -0.0628 0.6237 1.0000
1.500 0.4921 0.00668 0.00173 -0.0627 0.6179 1.0000
1.750 0.5195 0.00677 0.00178 -0.0626 0.6122 1.0000
2.000 0.5469 0.00683 0.00182 -0.0624 0.6052 1.0000
2.250 0.5743 0.00692 0.00187 -0.0623 0.5988 1.0000
2.500 0.6018 0.00697 0.00192 -0.0622 0.5911 1.0000
2.750 0.6291 0.00706 0.00198 -0.0621 0.5839 1.0000
3.000 0.6565 0.00712 0.00205 -0.0620 0.5758 1.0000
3.250 0.6839 0.00721 0.00213 -0.0619 0.5681 1.0000
3.500 0.7112 0.00729 0.00221 -0.0617 0.5600 1.0000
3.750 0.7386 0.00736 0.00230 -0.0617 0.5511 1.0000
4.000 0.7658 0.00746 0.00241 -0.0615 0.5419 1.0000
4.250 0.7929 0.00756 0.00251 -0.0614 0.5314 1.0000
4.500 0.8201 0.00765 0.00263 -0.0612 0.5202 1.0000
4.750 0.8471 0.00776 0.00276 -0.0611 0.5077 1.0000
5.000 0.8733 0.00791 0.00288 -0.0608 0.4864 1.0000
5.250 0.8990 0.00812 0.00301 -0.0605 0.4525 1.0000
5.500 0.9237 0.00847 0.00321 -0.0600 0.4094 1.0000
5.750 0.9460 0.00913 0.00356 -0.0594 0.3385 1.0000
6.000 0.9667 0.01004 0.00411 -0.0586 0.2620 1.0000
6.250 0.9870 0.01100 0.00472 -0.0579 0.1928 1.0000
6.500 1.0055 0.01215 0.00544 -0.0569 0.1169 1.0000
6.750 1.0218 0.01354 0.00635 -0.0556 0.0425 1.0000
7.000 1.0405 0.01462 0.00725 -0.0544 0.0153 1.0000
7.250 1.0629 0.01521 0.00792 -0.0537 0.0133 1.0000
7.500 1.0839 0.01594 0.00872 -0.0527 0.0120 1.0000
7.750 1.1015 0.01702 0.00992 -0.0513 0.0110 1.0000
8.000 1.1206 0.01785 0.01086 -0.0501 0.0107 1.0000
8.250 1.1377 0.01882 0.01193 -0.0487 0.0104 1.0000
8.500 1.1530 0.01991 0.01312 -0.0470 0.0102 1.0000
8.750 1.1666 0.02109 0.01442 -0.0452 0.0101 1.0000
9.000 1.1787 0.02237 0.01581 -0.0432 0.0101 1.0000
9.250 1.1895 0.02376 0.01730 -0.0410 0.0100 1.0000
9.500 1.1996 0.02502 0.01865 -0.0387 0.0098 1.0000
9.750 1.2096 0.02629 0.02003 -0.0365 0.0096 1.0000
10.000 1.2198 0.02770 0.02154 -0.0346 0.0094 1.0000
10.250 1.2304 0.02928 0.02325 -0.0327 0.0093 1.0000
10.500 1.2416 0.03125 0.02537 -0.0310 0.0093 1.0000
10.750 1.2517 0.03307 0.02734 -0.0295 0.0091 1.0000
11.000 1.2614 0.03565 0.03017 -0.0278 0.0094 1.0000
11.250 1.2671 0.03829 0.03304 -0.0261 0.0094 1.0000
11.500 1.2675 0.04171 0.03675 -0.0242 0.0097 1.0000
11.750 1.2625 0.04560 0.04092 -0.0225 0.0101 1.0000
12.000 1.2517 0.05009 0.04568 -0.0211 0.0105 1.0000
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Polar data table (+)
Polar graphs
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