E221 (9.39%) (e221-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: E221 (9.39%) (e221-il) Reynolds number: 100,000 Max Cl/Cd: 47.02 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e221-il-100000.txt Download as CSV file: xf-e221-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: E221 (9.39%)
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5119 0.09099 0.08648 -0.0051 1.0000 0.1081
-8.000 -0.5402 0.08704 0.08265 -0.0140 1.0000 0.1109
-7.750 -0.5391 0.08197 0.07761 -0.0155 1.0000 0.1130
-7.500 -0.5199 0.07905 0.07473 -0.0120 1.0000 0.1169
-7.250 -0.4505 0.06473 0.06076 -0.0153 1.0000 0.1294
-7.000 -0.5275 0.07010 0.06574 -0.0193 1.0000 0.1278
-6.750 -0.5137 0.06705 0.06271 -0.0181 1.0000 0.1329
-6.500 -0.5153 0.06261 0.05813 -0.0211 1.0000 0.1422
-6.250 -0.5015 0.05953 0.05508 -0.0203 1.0000 0.1483
-6.000 -0.4937 0.05600 0.05149 -0.0207 1.0000 0.1593
-5.750 -0.4879 0.04146 0.03526 -0.0235 1.0000 0.0693
-5.250 -0.4615 0.03323 0.02590 -0.0191 1.0000 0.0583
-5.000 -0.4453 0.03122 0.02354 -0.0170 1.0000 0.0578
-4.750 -0.4305 0.02863 0.02069 -0.0148 1.0000 0.0570
-4.500 -0.4172 0.02636 0.01814 -0.0123 1.0000 0.0566
-4.250 -0.4043 0.02465 0.01615 -0.0097 1.0000 0.0567
-4.000 -0.3905 0.02329 0.01452 -0.0072 1.0000 0.0574
-3.750 -0.3751 0.02141 0.01258 -0.0054 1.0000 0.0594
-3.500 -0.3606 0.02049 0.01165 -0.0037 1.0000 0.0645
-3.250 -0.3190 0.01892 0.01009 -0.0064 0.9918 0.0769
-3.000 -0.2759 0.01716 0.00858 -0.0094 0.9815 0.1223
-2.750 -0.2407 0.01459 0.00767 -0.0117 0.9714 0.3871
-2.500 -0.1594 0.01310 0.00800 -0.0182 0.9786 0.9244
-2.250 -0.0593 0.01319 0.00755 -0.0313 0.9861 1.0000
-2.000 0.0003 0.01309 0.00711 -0.0382 0.9724 1.0000
-1.750 0.0562 0.01295 0.00670 -0.0442 0.9576 1.0000
-1.500 0.1032 0.01283 0.00635 -0.0483 0.9388 1.0000
-1.250 0.1424 0.01275 0.00608 -0.0506 0.9189 1.0000
-1.000 0.1731 0.01273 0.00589 -0.0510 0.8995 1.0000
-0.750 0.1960 0.01282 0.00583 -0.0499 0.8787 1.0000
-0.500 0.2174 0.01292 0.00579 -0.0484 0.8600 1.0000
-0.250 0.2376 0.01305 0.00579 -0.0466 0.8429 1.0000
0.000 0.2577 0.01320 0.00582 -0.0447 0.8265 1.0000
0.250 0.2783 0.01338 0.00589 -0.0431 0.8099 1.0000
0.500 0.2993 0.01356 0.00597 -0.0416 0.7941 1.0000
0.750 0.3207 0.01374 0.00606 -0.0401 0.7789 1.0000
1.000 0.3424 0.01392 0.00617 -0.0386 0.7640 1.0000
1.250 0.3644 0.01411 0.00628 -0.0372 0.7494 1.0000
1.500 0.3867 0.01430 0.00640 -0.0359 0.7350 1.0000
1.750 0.4092 0.01448 0.00653 -0.0346 0.7208 1.0000
2.000 0.4320 0.01467 0.00669 -0.0333 0.7067 1.0000
2.250 0.4549 0.01486 0.00683 -0.0321 0.6926 1.0000
2.500 0.4780 0.01505 0.00698 -0.0308 0.6785 1.0000
2.750 0.5012 0.01524 0.00713 -0.0297 0.6643 1.0000
3.000 0.5245 0.01542 0.00729 -0.0285 0.6500 1.0000
3.250 0.5479 0.01561 0.00749 -0.0273 0.6353 1.0000
3.500 0.5714 0.01580 0.00767 -0.0262 0.6203 1.0000
3.750 0.5949 0.01598 0.00786 -0.0251 0.6049 1.0000
4.000 0.6185 0.01617 0.00806 -0.0240 0.5891 1.0000
4.250 0.6420 0.01635 0.00828 -0.0229 0.5729 1.0000
4.500 0.6656 0.01652 0.00847 -0.0218 0.5565 1.0000
4.750 0.6892 0.01668 0.00863 -0.0206 0.5396 1.0000
5.000 0.7128 0.01684 0.00880 -0.0194 0.5226 1.0000
5.250 0.7360 0.01704 0.00904 -0.0183 0.5036 1.0000
5.500 0.7590 0.01723 0.00927 -0.0171 0.4832 1.0000
5.750 0.7823 0.01740 0.00939 -0.0158 0.4635 1.0000
6.000 0.8044 0.01764 0.00974 -0.0146 0.4398 1.0000
6.250 0.8266 0.01788 0.01000 -0.0133 0.4160 1.0000
6.500 0.8482 0.01815 0.01024 -0.0120 0.3906 1.0000
6.750 0.8690 0.01848 0.01057 -0.0106 0.3624 1.0000
7.000 0.8890 0.01891 0.01104 -0.0092 0.3319 1.0000
7.250 0.9080 0.01944 0.01158 -0.0077 0.2990 1.0000
7.500 0.9259 0.02013 0.01218 -0.0062 0.2657 1.0000
7.750 0.9421 0.02096 0.01293 -0.0045 0.2292 1.0000
8.000 0.9560 0.02187 0.01369 -0.0029 0.1913 1.0000
8.250 0.9689 0.02302 0.01474 -0.0012 0.1549 1.0000
8.500 0.9792 0.02464 0.01622 0.0009 0.1218 1.0000
8.750 0.9872 0.02657 0.01799 0.0032 0.0923 1.0000
9.000 0.9965 0.02858 0.01985 0.0054 0.0757 1.0000
9.250 1.0110 0.03067 0.02198 0.0073 0.0667 1.0000
9.500 1.0288 0.03313 0.02432 0.0085 0.0609 1.0000
9.750 1.0452 0.03501 0.02650 0.0100 0.0565 1.0000
10.000 1.0608 0.03694 0.02850 0.0112 0.0525 1.0000
10.250 1.0808 0.04090 0.03253 0.0117 0.0501 1.0000
10.500 1.0909 0.04361 0.03566 0.0135 0.0494 1.0000
10.750 1.0964 0.04674 0.03921 0.0154 0.0488 1.0000
11.000 1.0970 0.05007 0.04293 0.0174 0.0486 1.0000
11.250 1.0915 0.05349 0.04672 0.0195 0.0484 1.0000
11.500 1.0796 0.05671 0.05023 0.0219 0.0484 1.0000
11.750 1.0639 0.05999 0.05377 0.0238 0.0483 1.0000
12.000 1.0453 0.06387 0.05789 0.0243 0.0483 1.0000
12.250 1.0274 0.06823 0.06245 0.0238 0.0486 1.0000
12.500 1.0064 0.07324 0.06765 0.0221 0.0488 1.0000
12.750 0.9881 0.07893 0.07347 0.0198 0.0494 1.0000
13.000 0.9656 0.08541 0.08009 0.0165 0.0497 1.0000
13.250 0.9472 0.09225 0.08702 0.0131 0.0502 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E221 (9.39%) (e221-il)