SD2030-086-88 (sd2030-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD2030-086-88 (sd2030-il) Reynolds number: 200,000 Max Cl/Cd: 77.26 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd2030-il-200000.txt Download as CSV file: xf-sd2030-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4528 0.09106 0.08761 -0.0395 1.0000 0.0475
-8.500 -0.4665 0.08802 0.08465 -0.0406 1.0000 0.0476
-8.250 -0.4824 0.08497 0.08164 -0.0414 1.0000 0.0477
-8.000 -0.4932 0.08171 0.07836 -0.0417 1.0000 0.0477
-7.750 -0.5032 0.07865 0.07525 -0.0412 1.0000 0.0478
-7.500 -0.5128 0.07253 0.06924 -0.0394 1.0000 0.0489
-7.250 -0.5121 0.07020 0.06696 -0.0366 1.0000 0.0497
-7.000 -0.5128 0.06796 0.06474 -0.0345 1.0000 0.0506
-6.750 -0.5142 0.06541 0.06217 -0.0330 1.0000 0.0516
-6.500 -0.5148 0.06257 0.05928 -0.0321 1.0000 0.0532
-6.250 -0.5136 0.05939 0.05602 -0.0316 1.0000 0.0554
-6.000 -0.5095 0.05706 0.05297 -0.0331 1.0000 0.0606
-5.750 -0.5076 0.05031 0.04637 -0.0327 1.0000 0.0625
-5.500 -0.4977 0.04813 0.04424 -0.0312 1.0000 0.0643
-5.250 -0.4862 0.04571 0.04172 -0.0303 1.0000 0.0667
-5.000 -0.4594 0.04122 0.03657 -0.0333 0.9973 0.0757
-4.750 -0.4311 0.03821 0.03359 -0.0352 0.9947 0.0784
-4.500 -0.4001 0.03539 0.03027 -0.0374 0.9907 0.0898
-4.250 -0.3640 0.02569 0.01932 -0.0365 0.9897 0.0426
-4.000 -0.3308 0.02312 0.01624 -0.0374 0.9871 0.0416
-3.750 -0.2956 0.02133 0.01406 -0.0387 0.9847 0.0419
-3.500 -0.2621 0.01973 0.01215 -0.0395 0.9820 0.0414
-3.250 -0.2308 0.01856 0.01082 -0.0400 0.9781 0.0420
-3.000 -0.1968 0.01764 0.00981 -0.0411 0.9747 0.0440
-2.750 -0.1599 0.01700 0.00908 -0.0429 0.9718 0.0472
-2.500 -0.1302 0.01619 0.00832 -0.0436 0.9673 0.0540
-2.250 -0.0980 0.01550 0.00766 -0.0445 0.9626 0.0678
-2.000 -0.0638 0.01418 0.00713 -0.0464 0.9594 0.2351
-1.750 -0.0381 0.01271 0.00724 -0.0467 0.9558 0.6156
-1.500 -0.0253 0.01224 0.00761 -0.0420 0.9489 0.8745
-1.250 0.0514 0.01233 0.00763 -0.0510 0.9519 0.9901
-1.000 0.0964 0.01238 0.00752 -0.0548 0.9481 1.0000
-0.750 0.1394 0.01241 0.00741 -0.0580 0.9444 1.0000
-0.500 0.1674 0.01238 0.00728 -0.0582 0.9362 1.0000
-0.250 0.2103 0.01232 0.00712 -0.0613 0.9317 1.0000
0.000 0.2471 0.01225 0.00699 -0.0631 0.9256 1.0000
0.250 0.2857 0.01211 0.00679 -0.0652 0.9191 1.0000
0.500 0.3380 0.01186 0.00651 -0.0699 0.9162 1.0000
0.750 0.3679 0.01169 0.00632 -0.0701 0.9070 1.0000
1.000 0.4144 0.01131 0.00594 -0.0734 0.9025 1.0000
1.250 0.4426 0.01110 0.00572 -0.0732 0.8928 1.0000
1.500 0.4854 0.01068 0.00530 -0.0756 0.8872 1.0000
1.750 0.5105 0.01047 0.00511 -0.0746 0.8756 1.0000
2.000 0.5377 0.01025 0.00490 -0.0739 0.8641 1.0000
2.250 0.5656 0.01003 0.00469 -0.0733 0.8520 1.0000
2.500 0.5925 0.00984 0.00451 -0.0726 0.8383 1.0000
2.750 0.6183 0.00970 0.00439 -0.0716 0.8226 1.0000
3.000 0.6441 0.00957 0.00426 -0.0706 0.8045 1.0000
3.250 0.6682 0.00951 0.00418 -0.0693 0.7828 1.0000
3.500 0.6923 0.00947 0.00411 -0.0680 0.7565 1.0000
3.750 0.7150 0.00950 0.00411 -0.0665 0.7243 1.0000
4.000 0.7375 0.00959 0.00410 -0.0650 0.6831 1.0000
4.250 0.7587 0.00982 0.00413 -0.0632 0.6302 1.0000
4.500 0.7773 0.01024 0.00426 -0.0610 0.5647 1.0000
4.750 0.7937 0.01083 0.00452 -0.0587 0.4941 1.0000
5.000 0.8096 0.01150 0.00486 -0.0564 0.4264 1.0000
5.250 0.8260 0.01221 0.00527 -0.0544 0.3640 1.0000
5.500 0.8432 0.01292 0.00571 -0.0526 0.3081 1.0000
5.750 0.8610 0.01365 0.00619 -0.0510 0.2592 1.0000
6.000 0.8793 0.01440 0.00674 -0.0495 0.2158 1.0000
6.250 0.8982 0.01514 0.00733 -0.0481 0.1787 1.0000
6.500 0.9166 0.01597 0.00798 -0.0467 0.1485 1.0000
6.750 0.9356 0.01678 0.00871 -0.0453 0.1250 1.0000
7.000 0.9543 0.01765 0.00949 -0.0439 0.1083 1.0000
7.250 0.9734 0.01854 0.01039 -0.0425 0.0957 1.0000
7.500 0.9926 0.01945 0.01132 -0.0412 0.0854 1.0000
7.750 1.0112 0.02058 0.01241 -0.0398 0.0773 1.0000
8.000 1.0313 0.02129 0.01318 -0.0387 0.0689 1.0000
8.250 1.0506 0.02214 0.01412 -0.0375 0.0605 1.0000
8.500 1.0682 0.02326 0.01527 -0.0362 0.0529 1.0000
8.750 1.0865 0.02394 0.01605 -0.0348 0.0455 1.0000
9.000 1.1028 0.02522 0.01745 -0.0332 0.0377 1.0000
9.250 1.1178 0.02738 0.01961 -0.0316 0.0324 1.0000
9.500 1.1354 0.02883 0.02129 -0.0300 0.0287 1.0000
9.750 1.1511 0.03023 0.02279 -0.0285 0.0263 1.0000
10.000 1.1645 0.03308 0.02581 -0.0270 0.0238 1.0000
10.250 1.1773 0.03465 0.02770 -0.0250 0.0223 1.0000
10.500 1.1878 0.03708 0.03044 -0.0229 0.0215 1.0000
10.750 1.1934 0.03959 0.03326 -0.0203 0.0208 1.0000
11.000 1.1947 0.04219 0.03615 -0.0173 0.0204 1.0000
11.250 1.1914 0.04500 0.03926 -0.0141 0.0201 1.0000
11.500 1.1840 0.04798 0.04253 -0.0110 0.0199 1.0000
11.750 1.1729 0.05121 0.04604 -0.0081 0.0197 1.0000
12.000 1.1529 0.05547 0.05066 -0.0056 0.0200 1.0000
12.250 1.1315 0.06001 0.05550 -0.0042 0.0202 1.0000
12.500 1.1082 0.06514 0.06090 -0.0042 0.0204 1.0000
12.750 1.0817 0.07134 0.06736 -0.0057 0.0206 1.0000
13.000 1.0545 0.07858 0.07483 -0.0092 0.0209 1.0000
13.250 1.0269 0.08717 0.08362 -0.0147 0.0212 1.0000
13.500 0.9959 0.09832 0.09493 -0.0227 0.0218 1.0000
13.750 0.9601 0.11299 0.10969 -0.0329 0.0226 1.0000
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Polar data table (+)
Polar graphs
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