SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD2030-086-88 (sd2030-il) Reynolds number: 500,000 Max Cl/Cd: 104.79 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd2030-il-500000.txt Download as CSV file: xf-sd2030-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SD2030-086-88
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4600 0.08390 0.08170 -0.0379 1.0000 0.0199
-8.750 -0.4681 0.08110 0.07892 -0.0369 1.0000 0.0203
-8.500 -0.4792 0.07824 0.07611 -0.0363 1.0000 0.0204
-8.250 -0.5042 0.07512 0.07307 -0.0353 1.0000 0.0203
-8.000 -0.5223 0.07185 0.06982 -0.0353 1.0000 0.0203
-7.750 -0.5298 0.06815 0.06611 -0.0360 0.9996 0.0204
-7.500 -0.5112 0.06426 0.06216 -0.0408 0.9968 0.0211
-7.250 -0.4903 0.05893 0.05673 -0.0473 0.9938 0.0218
-7.000 -0.4712 0.05356 0.05122 -0.0525 0.9894 0.0227
-6.750 -0.4471 0.04732 0.04473 -0.0579 0.9859 0.0246
-6.500 -0.4125 0.04247 0.03928 -0.0621 0.9835 0.0269
-6.250 -0.4073 0.03456 0.03113 -0.0637 0.9770 0.0286
-6.000 -0.3796 0.03276 0.02923 -0.0655 0.9746 0.0300
-5.750 -0.3497 0.03030 0.02655 -0.0674 0.9727 0.0323
-5.500 -0.3100 0.03124 0.02706 -0.0685 0.9714 0.0363
-5.000 -0.2724 0.01607 0.01034 -0.0663 0.9624 0.0209
-4.750 -0.2396 0.01478 0.00891 -0.0675 0.9608 0.0213
-4.500 -0.2054 0.01376 0.00778 -0.0689 0.9595 0.0218
-4.250 -0.1702 0.01296 0.00691 -0.0705 0.9585 0.0226
-4.000 -0.1346 0.01232 0.00623 -0.0722 0.9575 0.0240
-3.750 -0.1119 0.01173 0.00558 -0.0711 0.9514 0.0246
-3.500 -0.0804 0.01116 0.00495 -0.0718 0.9485 0.0258
-3.250 -0.0473 0.01070 0.00444 -0.0729 0.9464 0.0268
-3.000 -0.0143 0.01009 0.00379 -0.0739 0.9444 0.0312
-2.750 0.0138 0.00972 0.00344 -0.0739 0.9402 0.0419
-2.500 0.0400 0.00912 0.00314 -0.0737 0.9350 0.1160
-2.250 0.0694 0.00855 0.00291 -0.0742 0.9316 0.2085
-2.000 0.0978 0.00787 0.00271 -0.0746 0.9284 0.3525
-1.750 0.1185 0.00716 0.00258 -0.0734 0.9209 0.5257
-1.500 0.1414 0.00637 0.00250 -0.0721 0.9162 0.7340
-1.250 0.1619 0.00613 0.00254 -0.0699 0.9088 0.8309
-1.000 0.1875 0.00601 0.00246 -0.0688 0.9030 0.8696
-0.750 0.2118 0.00595 0.00240 -0.0676 0.8955 0.8916
-0.500 0.2362 0.00589 0.00233 -0.0662 0.8886 0.9160
-0.250 0.2592 0.00587 0.00231 -0.0646 0.8801 0.9369
0.000 0.2871 0.00583 0.00222 -0.0641 0.8730 0.9527
0.250 0.3188 0.00583 0.00220 -0.0645 0.8637 0.9659
0.500 0.3577 0.00583 0.00214 -0.0666 0.8556 0.9748
0.750 0.3990 0.00583 0.00210 -0.0693 0.8459 0.9814
1.000 0.4416 0.00582 0.00206 -0.0724 0.8348 0.9863
1.250 0.4823 0.00582 0.00201 -0.0751 0.8230 0.9913
1.500 0.5211 0.00582 0.00198 -0.0775 0.8099 0.9960
1.750 0.5588 0.00582 0.00193 -0.0796 0.7937 1.0000
2.000 0.5798 0.00585 0.00190 -0.0782 0.7762 1.0000
2.250 0.6001 0.00589 0.00189 -0.0766 0.7552 1.0000
2.500 0.6200 0.00598 0.00190 -0.0749 0.7306 1.0000
2.750 0.6392 0.00610 0.00192 -0.0731 0.6996 1.0000
3.000 0.6570 0.00630 0.00196 -0.0709 0.6595 1.0000
3.250 0.6743 0.00657 0.00204 -0.0688 0.6135 1.0000
3.500 0.6906 0.00694 0.00217 -0.0664 0.5591 1.0000
3.750 0.7074 0.00738 0.00237 -0.0642 0.4990 1.0000
4.000 0.7259 0.00785 0.00258 -0.0625 0.4427 1.0000
4.250 0.7452 0.00834 0.00282 -0.0610 0.3861 1.0000
4.500 0.7658 0.00882 0.00307 -0.0597 0.3353 1.0000
4.750 0.7869 0.00930 0.00335 -0.0586 0.2884 1.0000
5.000 0.8089 0.00974 0.00363 -0.0577 0.2496 1.0000
5.250 0.8311 0.01019 0.00392 -0.0568 0.2154 1.0000
5.500 0.8536 0.01063 0.00423 -0.0560 0.1830 1.0000
5.750 0.8760 0.01109 0.00457 -0.0552 0.1543 1.0000
6.000 0.8985 0.01155 0.00493 -0.0543 0.1296 1.0000
6.250 0.9208 0.01203 0.00531 -0.0535 0.1078 1.0000
6.500 0.9430 0.01253 0.00573 -0.0526 0.0901 1.0000
6.750 0.9653 0.01301 0.00617 -0.0518 0.0762 1.0000
7.000 0.9873 0.01353 0.00665 -0.0509 0.0649 1.0000
7.250 1.0092 0.01403 0.00711 -0.0500 0.0552 1.0000
7.500 1.0325 0.01440 0.00752 -0.0493 0.0494 1.0000
7.750 1.0529 0.01505 0.00815 -0.0482 0.0429 1.0000
8.000 1.0765 0.01536 0.00853 -0.0476 0.0393 1.0000
8.250 1.0966 0.01601 0.00918 -0.0465 0.0332 1.0000
8.500 1.1198 0.01634 0.00955 -0.0459 0.0280 1.0000
8.750 1.1398 0.01700 0.01019 -0.0447 0.0204 1.0000
9.000 1.1574 0.01791 0.01112 -0.0431 0.0154 1.0000
9.250 1.1748 0.01878 0.01203 -0.0416 0.0134 1.0000
9.500 1.1889 0.01993 0.01330 -0.0395 0.0121 1.0000
9.750 1.2054 0.02078 0.01428 -0.0378 0.0113 1.0000
10.000 1.2204 0.02169 0.01527 -0.0359 0.0105 1.0000
10.250 1.2329 0.02264 0.01631 -0.0337 0.0098 1.0000
10.500 1.2424 0.02380 0.01757 -0.0310 0.0096 1.0000
10.750 1.2473 0.02541 0.01931 -0.0278 0.0092 1.0000
11.000 1.2485 0.02754 0.02162 -0.0244 0.0089 1.0000
11.250 1.2537 0.02933 0.02359 -0.0217 0.0087 1.0000
11.500 1.2637 0.03041 0.02481 -0.0196 0.0085 1.0000
11.750 1.2703 0.03185 0.02642 -0.0174 0.0082 1.0000
12.000 1.2754 0.03344 0.02818 -0.0152 0.0080 1.0000
12.250 1.2761 0.03558 0.03052 -0.0128 0.0079 1.0000
12.500 1.2751 0.03787 0.03300 -0.0107 0.0079 1.0000
12.750 1.2728 0.04032 0.03565 -0.0087 0.0077 1.0000
13.000 1.2659 0.04340 0.03895 -0.0070 0.0077 1.0000
13.250 1.2594 0.04648 0.04222 -0.0058 0.0077 1.0000
13.500 1.2498 0.05012 0.04607 -0.0052 0.0076 1.0000
13.750 1.2365 0.05450 0.05066 -0.0052 0.0076 1.0000
14.000 1.2215 0.05948 0.05586 -0.0062 0.0076 1.0000
14.250 1.2081 0.06462 0.06118 -0.0080 0.0075 1.0000
14.500 1.1875 0.07159 0.06837 -0.0113 0.0076 1.0000
14.750 1.1702 0.07867 0.07564 -0.0153 0.0077 1.0000
15.000 1.1513 0.08685 0.08399 -0.0204 0.0076 1.0000
15.250 1.1261 0.09717 0.09451 -0.0270 0.0077 1.0000
15.500 1.1038 0.10749 0.10498 -0.0336 0.0078 1.0000
15.750 1.0717 0.12080 0.11846 -0.0418 0.0080 1.0000
16.000 1.0391 0.13508 0.13285 -0.0503 0.0082 1.0000
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Polar data table (+)
Polar graphs
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